NACA 66(4)-221 (naca664221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(4)-221 (naca664221-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.81 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca664221-il-1000000.txt Download as CSV file: xf-naca664221-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(4)-221
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9012 0.07101 0.06666 -0.1106 0.8986 0.0173
-19.500 -0.9028 0.06802 0.06352 -0.1113 0.8892 0.0173
-19.250 -0.9047 0.06516 0.06050 -0.1116 0.8807 0.0174
-19.000 -0.9055 0.06242 0.05764 -0.1118 0.8742 0.0176
-18.750 -0.9038 0.06006 0.05518 -0.1119 0.8673 0.0178
-18.500 -0.9004 0.05788 0.05290 -0.1121 0.8607 0.0179
-18.250 -0.8952 0.05585 0.05078 -0.1122 0.8554 0.0178
-18.000 -0.8908 0.05384 0.04869 -0.1122 0.8497 0.0180
-17.750 -0.8849 0.05202 0.04679 -0.1122 0.8440 0.0181
-17.500 -0.8788 0.05019 0.04489 -0.1122 0.8398 0.0183
-17.250 -0.8718 0.04848 0.04311 -0.1120 0.8353 0.0183
-17.000 -0.8638 0.04692 0.04148 -0.1119 0.8306 0.0186
-16.750 -0.8558 0.04542 0.03990 -0.1116 0.8259 0.0187
-16.500 -0.8472 0.04395 0.03836 -0.1113 0.8222 0.0189
-16.250 -0.8375 0.04257 0.03692 -0.1110 0.8187 0.0190
-16.000 -0.8280 0.04123 0.03552 -0.1106 0.8150 0.0192
-15.750 -0.8177 0.03999 0.03420 -0.1101 0.8111 0.0194
-15.500 -0.8077 0.03879 0.03291 -0.1095 0.8070 0.0196
-15.250 -0.7971 0.03759 0.03166 -0.1090 0.8038 0.0198
-15.000 -0.7859 0.03646 0.03047 -0.1085 0.8011 0.0199
-14.750 -0.7746 0.03535 0.02931 -0.1078 0.7981 0.0200
-14.500 -0.7623 0.03434 0.02824 -0.1072 0.7950 0.0202
-14.250 -0.7500 0.03337 0.02720 -0.1066 0.7920 0.0204
-14.000 -0.7364 0.03252 0.02628 -0.1060 0.7887 0.0205
-13.750 -0.7237 0.03160 0.02531 -0.1053 0.7859 0.0206
-13.500 -0.7202 0.03010 0.02377 -0.1037 0.7840 0.0211
-13.250 -0.7091 0.02911 0.02276 -0.1028 0.7818 0.0214
-13.000 -0.6963 0.02824 0.02186 -0.1020 0.7796 0.0215
-12.750 -0.6816 0.02750 0.02110 -0.1013 0.7773 0.0220
-12.500 -0.6677 0.02675 0.02031 -0.1004 0.7749 0.0223
-12.250 -0.6539 0.02600 0.01951 -0.0995 0.7726 0.0228
-12.000 -0.6386 0.02536 0.01882 -0.0988 0.7700 0.0232
-11.750 -0.6239 0.02468 0.01809 -0.0979 0.7676 0.0235
-11.500 -0.6071 0.02410 0.01748 -0.0973 0.7664 0.0239
-11.250 -0.5945 0.02331 0.01667 -0.0961 0.7649 0.0244
-11.000 -0.5813 0.02258 0.01592 -0.0950 0.7632 0.0251
-10.750 -0.5651 0.02201 0.01535 -0.0941 0.7616 0.0260
-10.500 -0.5487 0.02146 0.01478 -0.0933 0.7599 0.0267
-10.250 -0.5320 0.02094 0.01423 -0.0925 0.7583 0.0274
-10.000 -0.5134 0.02052 0.01378 -0.0918 0.7568 0.0280
-9.750 -0.5005 0.01985 0.01309 -0.0904 0.7551 0.0293
-9.500 -0.4835 0.01938 0.01261 -0.0896 0.7534 0.0305
-9.250 -0.4664 0.01894 0.01214 -0.0887 0.7515 0.0315
-9.000 -0.4495 0.01851 0.01168 -0.0877 0.7497 0.0330
-8.750 -0.4333 0.01801 0.01121 -0.0867 0.7489 0.0351
-8.500 -0.4152 0.01761 0.01080 -0.0858 0.7480 0.0369
-8.250 -0.3990 0.01714 0.01035 -0.0847 0.7470 0.0397
-8.000 -0.3819 0.01672 0.00994 -0.0836 0.7458 0.0431
-7.750 -0.3664 0.01625 0.00951 -0.0824 0.7446 0.0499
-7.500 -0.3527 0.01571 0.00907 -0.0808 0.7433 0.0642
-7.250 -0.3431 0.01505 0.00854 -0.0787 0.7420 0.0905
-7.000 -0.3388 0.01423 0.00794 -0.0757 0.7408 0.1333
-6.750 -0.3359 0.01340 0.00733 -0.0725 0.7396 0.1794
-6.500 -0.3348 0.01256 0.00670 -0.0689 0.7384 0.2270
-6.250 -0.3367 0.01167 0.00604 -0.0647 0.7371 0.2758
-6.000 -0.3402 0.01081 0.00537 -0.0601 0.7357 0.3228
-5.750 -0.3504 0.00987 0.00464 -0.0542 0.7342 0.3749
-5.500 -0.3588 0.00919 0.00411 -0.0482 0.7324 0.4142
-5.250 -0.3743 0.00872 0.00380 -0.0403 0.7313 0.4558
-5.000 -0.3819 0.00799 0.00338 -0.0341 0.7306 0.5250
-4.750 -0.3793 0.00739 0.00318 -0.0296 0.7298 0.6167
-4.500 -0.3539 0.00740 0.00323 -0.0294 0.7292 0.6432
-4.250 -0.3263 0.00743 0.00325 -0.0297 0.7286 0.6546
-4.000 -0.2983 0.00750 0.00330 -0.0300 0.7279 0.6641
-3.750 -0.2704 0.00761 0.00342 -0.0302 0.7273 0.6740
-3.500 -0.2418 0.00776 0.00356 -0.0305 0.7266 0.6817
-3.250 -0.2133 0.00788 0.00366 -0.0309 0.7260 0.6883
-3.000 -0.1834 0.00803 0.00384 -0.0315 0.7253 0.6932
-2.750 -0.1537 0.00819 0.00400 -0.0320 0.7246 0.6978
-2.500 -0.1247 0.00835 0.00413 -0.0325 0.7238 0.7018
-2.250 -0.0959 0.00838 0.00413 -0.0330 0.7231 0.7046
-2.000 -0.0660 0.00842 0.00420 -0.0337 0.7225 0.7077
-1.750 -0.0359 0.00851 0.00430 -0.0344 0.7219 0.7098
-1.500 -0.0064 0.00854 0.00432 -0.0350 0.7213 0.7111
-1.250 0.0232 0.00858 0.00436 -0.0357 0.7207 0.7124
-1.000 0.0527 0.00865 0.00442 -0.0363 0.7201 0.7143
-0.750 0.0822 0.00873 0.00449 -0.0370 0.7196 0.7164
-0.500 0.1115 0.00879 0.00454 -0.0376 0.7190 0.7180
-0.250 0.1408 0.00881 0.00455 -0.0383 0.7184 0.7188
0.000 0.1701 0.00882 0.00454 -0.0390 0.7178 0.7193
0.250 0.1995 0.00884 0.00455 -0.0397 0.7170 0.7198
0.500 0.2287 0.00889 0.00459 -0.0404 0.7161 0.7203
0.750 0.2574 0.00903 0.00472 -0.0410 0.7146 0.7207
1.000 0.2859 0.00902 0.00472 -0.0415 0.7135 0.7211
1.250 0.3142 0.00890 0.00462 -0.0419 0.7121 0.7216
1.500 0.3423 0.00877 0.00450 -0.0424 0.7104 0.7225
1.750 0.3709 0.00870 0.00445 -0.0429 0.7089 0.7233
2.000 0.3997 0.00867 0.00443 -0.0434 0.7075 0.7240
2.250 0.4288 0.00861 0.00439 -0.0440 0.7058 0.7246
2.500 0.4587 0.00853 0.00431 -0.0447 0.7037 0.7253
2.750 0.4892 0.00843 0.00421 -0.0456 0.7014 0.7259
3.000 0.5194 0.00841 0.00418 -0.0463 0.6992 0.7265
3.250 0.5487 0.00849 0.00427 -0.0470 0.6966 0.7271
3.500 0.5751 0.00836 0.00420 -0.0470 0.6939 0.7278
3.750 0.6025 0.00824 0.00410 -0.0471 0.6900 0.7285
4.000 0.6314 0.00810 0.00397 -0.0476 0.6856 0.7293
4.250 0.6611 0.00803 0.00388 -0.0482 0.6808 0.7301
4.500 0.6850 0.00793 0.00383 -0.0476 0.6752 0.7309
4.750 0.7098 0.00781 0.00373 -0.0472 0.6678 0.7316
5.000 0.7331 0.00773 0.00366 -0.0465 0.6585 0.7324
5.250 0.7549 0.00769 0.00361 -0.0455 0.6475 0.7332
5.500 0.7742 0.00768 0.00362 -0.0440 0.6319 0.7341
5.750 0.7762 0.00780 0.00362 -0.0390 0.5921 0.7351
6.000 0.7522 0.00836 0.00398 -0.0290 0.5527 0.7364
6.250 0.7308 0.00933 0.00475 -0.0203 0.5110 0.7376
6.500 0.7159 0.01037 0.00562 -0.0133 0.4738 0.7386
6.750 0.7007 0.01160 0.00667 -0.0066 0.4334 0.7394
7.000 0.6922 0.01272 0.00763 -0.0013 0.3971 0.7411
7.250 0.6852 0.01388 0.00864 0.0036 0.3595 0.7429
7.500 0.6828 0.01496 0.00956 0.0076 0.3238 0.7444
7.750 0.6800 0.01611 0.01053 0.0115 0.2838 0.7459
8.000 0.6818 0.01715 0.01141 0.0147 0.2489 0.7472
8.250 0.6838 0.01822 0.01228 0.0177 0.2090 0.7485
8.500 0.6878 0.01926 0.01315 0.0204 0.1739 0.7499
8.750 0.6919 0.02032 0.01402 0.0229 0.1370 0.7512
9.000 0.6972 0.02138 0.01488 0.0253 0.1015 0.7526
9.250 0.7039 0.02241 0.01576 0.0273 0.0741 0.7540
9.500 0.7135 0.02333 0.01655 0.0290 0.0533 0.7554
9.750 0.7265 0.02412 0.01726 0.0302 0.0421 0.7566
10.000 0.7413 0.02483 0.01794 0.0312 0.0369 0.7577
10.250 0.7561 0.02555 0.01865 0.0322 0.0334 0.7589
10.500 0.7704 0.02628 0.01938 0.0332 0.0306 0.7612
10.750 0.7872 0.02688 0.02002 0.0338 0.0289 0.7632
11.000 0.8009 0.02768 0.02082 0.0349 0.0266 0.7651
11.250 0.8169 0.02838 0.02155 0.0356 0.0255 0.7669
11.500 0.8314 0.02917 0.02237 0.0364 0.0238 0.7687
11.750 0.8449 0.03005 0.02326 0.0373 0.0224 0.7705
12.000 0.8612 0.03077 0.02401 0.0379 0.0214 0.7724
12.250 0.8761 0.03159 0.02485 0.0385 0.0209 0.7742
12.500 0.8892 0.03253 0.02581 0.0393 0.0200 0.7758
12.750 0.9008 0.03361 0.02690 0.0402 0.0195 0.7773
13.000 0.9145 0.03453 0.02787 0.0409 0.0188 0.7801
13.250 0.9284 0.03543 0.02883 0.0416 0.0182 0.7829
13.500 0.9410 0.03646 0.02992 0.0423 0.0181 0.7854
13.750 0.9534 0.03752 0.03103 0.0430 0.0178 0.7880
14.000 0.9663 0.03857 0.03210 0.0435 0.0171 0.7906
14.250 0.9762 0.03987 0.03343 0.0443 0.0166 0.7930
14.500 0.9853 0.04127 0.03488 0.0450 0.0166 0.7953
14.750 0.9901 0.04303 0.03669 0.0460 0.0162 0.7975
15.000 0.9998 0.04440 0.03814 0.0466 0.0161 0.8012
15.250 1.0124 0.04556 0.03937 0.0470 0.0158 0.8046
15.500 1.0213 0.04706 0.04094 0.0475 0.0157 0.8078
15.750 1.0299 0.04863 0.04257 0.0480 0.0155 0.8111
16.000 1.0384 0.05026 0.04426 0.0484 0.0154 0.8141
16.250 1.0459 0.05200 0.04606 0.0487 0.0153 0.8171
16.500 1.0553 0.05356 0.04769 0.0490 0.0149 0.8213
16.750 1.0618 0.05542 0.04964 0.0493 0.0148 0.8252
17.000 1.0662 0.05753 0.05183 0.0495 0.0149 0.8292
17.250 1.0733 0.05946 0.05382 0.0496 0.0147 0.8330
17.500 1.0799 0.06147 0.05590 0.0496 0.0145 0.8371
17.750 1.0862 0.06349 0.05800 0.0495 0.0144 0.8421
18.000 1.0897 0.06587 0.06046 0.0495 0.0142 0.8471
18.250 1.0933 0.06831 0.06297 0.0492 0.0142 0.8515
18.500 1.0975 0.07066 0.06541 0.0490 0.0141 0.8571
18.750 1.0996 0.07330 0.06813 0.0487 0.0139 0.8629
19.000 1.0976 0.07643 0.07134 0.0483 0.0136 0.8684
19.250 1.1029 0.07880 0.07381 0.0478 0.0138 0.8753
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(4)-221 (naca664221-il)