NACA 66(4)-221 (naca664221-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(4)-221 (naca664221-il) Reynolds number: 100,000 Max Cl/Cd: 18.07 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca664221-il-100000-n5.txt Download as CSV file: xf-naca664221-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.5636 0.10668 0.10074 -0.0994 0.9600 0.0372
-17.250 -0.5891 0.09776 0.09160 -0.1054 0.9549 0.0370
-17.000 -0.6180 0.08940 0.08294 -0.1105 0.9496 0.0369
-16.750 -0.6429 0.08240 0.07562 -0.1145 0.9447 0.0370
-16.500 -0.6627 0.07694 0.06987 -0.1166 0.9385 0.0370
-16.250 -0.6781 0.07231 0.06494 -0.1181 0.9329 0.0371
-16.000 -0.6934 0.06819 0.06048 -0.1188 0.9274 0.0372
-15.750 -0.7008 0.06495 0.05701 -0.1188 0.9214 0.0374
-15.500 -0.6982 0.06238 0.05426 -0.1189 0.9164 0.0377
-15.250 -0.6953 0.06002 0.05173 -0.1188 0.9115 0.0379
-15.000 -0.6917 0.05785 0.04939 -0.1183 0.9061 0.0382
-14.750 -0.6854 0.05584 0.04720 -0.1179 0.9014 0.0386
-14.500 -0.6771 0.05396 0.04513 -0.1175 0.8975 0.0390
-14.250 -0.6677 0.05223 0.04324 -0.1170 0.8929 0.0396
-14.000 -0.6554 0.05063 0.04146 -0.1165 0.8886 0.0401
-13.750 -0.6406 0.04916 0.03981 -0.1162 0.8850 0.0407
-13.500 -0.6264 0.04772 0.03814 -0.1157 0.8818 0.0419
-13.250 -0.6097 0.04647 0.03671 -0.1154 0.8790 0.0429
-13.000 -0.5890 0.04551 0.03577 -0.1155 0.8757 0.0439
-12.750 -0.5711 0.04457 0.03479 -0.1152 0.8724 0.0452
-12.500 -0.5512 0.04368 0.03381 -0.1150 0.8694 0.0465
-12.250 -0.5303 0.04285 0.03287 -0.1148 0.8668 0.0479
-12.000 -0.5097 0.04208 0.03203 -0.1145 0.8644 0.0491
-11.750 -0.4929 0.04122 0.03119 -0.1141 0.8622 0.0508
-11.500 -0.4765 0.04044 0.03037 -0.1136 0.8598 0.0527
-11.250 -0.4604 0.03971 0.02955 -0.1131 0.8570 0.0552
-11.000 -0.4472 0.03886 0.02873 -0.1123 0.8541 0.0573
-10.750 -0.4341 0.03806 0.02791 -0.1114 0.8514 0.0601
-10.500 -0.4209 0.03730 0.02707 -0.1104 0.8487 0.0631
-10.250 -0.4098 0.03644 0.02620 -0.1092 0.8464 0.0664
-10.000 -0.3969 0.03569 0.02536 -0.1081 0.8443 0.0714
-9.750 -0.3862 0.03485 0.02456 -0.1067 0.8423 0.0775
-9.500 -0.3754 0.03416 0.02392 -0.1055 0.8398 0.0857
-9.250 -0.3651 0.03345 0.02332 -0.1041 0.8373 0.1000
-9.000 -0.3566 0.03266 0.02276 -0.1024 0.8349 0.1303
-8.750 -0.3511 0.03175 0.02224 -0.1004 0.8326 0.1858
-8.500 -0.3489 0.03082 0.02170 -0.0978 0.8304 0.2515
-8.250 -0.3473 0.02999 0.02124 -0.0950 0.8283 0.3167
-8.000 -0.3414 0.02950 0.02116 -0.0922 0.8266 0.3861
-7.750 -0.3129 0.03028 0.02235 -0.0912 0.8255 0.4631
-7.500 -0.2678 0.03220 0.02446 -0.0916 0.8247 0.5185
-7.250 -0.2418 0.03364 0.02592 -0.0902 0.8232 0.5563
-7.000 -0.2213 0.03520 0.02745 -0.0881 0.8207 0.5795
-6.750 -0.2048 0.03613 0.02832 -0.0861 0.8180 0.5954
-6.500 -0.1921 0.03657 0.02867 -0.0840 0.8157 0.6075
-6.250 -0.1861 0.03680 0.02883 -0.0812 0.8134 0.6205
-5.750 -0.1501 0.03771 0.02956 -0.0784 0.8102 0.6380
-5.500 -0.1438 0.03788 0.02964 -0.0754 0.8085 0.6496
-5.250 -0.1156 0.03837 0.03003 -0.0755 0.8075 0.6547
-4.750 -0.0844 0.03884 0.03034 -0.0722 0.8051 0.6705
-4.250 -0.1159 0.04093 0.03250 -0.0587 0.7960 0.6872
-4.000 -0.0905 0.04157 0.03308 -0.0584 0.7945 0.6905
-3.750 -0.1090 0.04186 0.03336 -0.0513 0.7915 0.7018
-3.500 -0.0831 0.04209 0.03351 -0.0512 0.7901 0.7057
-3.250 -0.0507 0.04234 0.03369 -0.0522 0.7891 0.7087
-3.000 -0.0746 0.04215 0.03346 -0.0442 0.7870 0.7211
-1.500 -0.2068 0.04445 0.03580 0.0045 0.7598 0.7596
-1.250 -0.1820 0.04473 0.03603 0.0046 0.7572 0.7615
-1.000 -0.1559 0.04487 0.03614 0.0045 0.7550 0.7638
-0.750 -0.1343 0.04487 0.03609 0.0051 0.7531 0.7669
-0.250 -0.1745 0.04393 0.03510 0.0197 0.7431 0.7796
0.000 -0.1578 0.04404 0.03518 0.0210 0.7394 0.7815
0.250 -0.1365 0.04396 0.03507 0.0216 0.7366 0.7835
0.500 -0.1138 0.04380 0.03487 0.0220 0.7345 0.7858
0.750 -0.0904 0.04352 0.03456 0.0222 0.7328 0.7883
1.000 -0.1338 0.04274 0.03374 0.0325 0.7231 0.7955
1.250 -0.1184 0.04237 0.03334 0.0337 0.7195 0.7976
1.500 -0.0911 0.04232 0.03328 0.0334 0.7172 0.7988
1.750 -0.0612 0.04221 0.03316 0.0326 0.7154 0.8000
2.250 -0.0488 0.04227 0.03323 0.0379 0.7028 0.8033
2.500 -0.0232 0.04212 0.03307 0.0377 0.7001 0.8049
2.750 0.0059 0.04192 0.03287 0.0370 0.6981 0.8065
3.250 0.0229 0.04185 0.03281 0.0410 0.6849 0.8105
3.500 0.0515 0.04157 0.03254 0.0403 0.6822 0.8119
3.750 0.0828 0.04126 0.03224 0.0391 0.6803 0.8132
4.000 0.0793 0.04150 0.03248 0.0422 0.6693 0.8159
4.250 0.1080 0.04136 0.03238 0.0418 0.6661 0.8169
4.500 0.1399 0.04115 0.03222 0.0409 0.6639 0.8179
4.750 0.1416 0.04159 0.03271 0.0437 0.6531 0.8194
5.000 0.1707 0.04138 0.03255 0.0431 0.6496 0.8204
5.250 0.2038 0.04105 0.03228 0.0421 0.6473 0.8215
5.500 0.2067 0.04150 0.03279 0.0446 0.6357 0.8232
5.750 0.2379 0.04118 0.03253 0.0438 0.6325 0.8244
6.250 0.2759 0.04122 0.03271 0.0448 0.6178 0.8276
6.750 0.3177 0.04114 0.03276 0.0454 0.6029 0.8310
7.250 0.3629 0.04089 0.03267 0.0456 0.5876 0.8349
7.750 0.4076 0.04049 0.03250 0.0466 0.5719 0.8379
8.250 0.4543 0.03992 0.03216 0.0474 0.5556 0.8411
8.750 0.5043 0.03907 0.03155 0.0480 0.5376 0.8448
9.000 0.5264 0.03868 0.03126 0.0486 0.5222 0.8469
9.250 0.5571 0.03736 0.02995 0.0490 0.4975 0.8489
9.500 0.5880 0.03611 0.02857 0.0494 0.4574 0.8511
9.750 0.6192 0.03513 0.02735 0.0496 0.4096 0.8530
10.000 0.6365 0.03523 0.02726 0.0509 0.3657 0.8549
10.250 0.6468 0.03589 0.02767 0.0526 0.3187 0.8570
10.500 0.6522 0.03700 0.02853 0.0544 0.2713 0.8594
10.750 0.6562 0.03834 0.02960 0.0561 0.2241 0.8621
11.000 0.6582 0.03992 0.03089 0.0577 0.1747 0.8652
11.250 0.6615 0.04157 0.03223 0.0591 0.1305 0.8683
11.500 0.6662 0.04318 0.03360 0.0602 0.1000 0.8712
11.750 0.6723 0.04462 0.03496 0.0615 0.0835 0.8739
12.000 0.6791 0.04608 0.03639 0.0626 0.0730 0.8769
12.250 0.6869 0.04753 0.03783 0.0634 0.0666 0.8801
12.500 0.6951 0.04904 0.03937 0.0641 0.0609 0.8835
12.750 0.7041 0.05055 0.04092 0.0646 0.0570 0.8869
13.000 0.7118 0.05206 0.04249 0.0653 0.0535 0.8901
13.250 0.7199 0.05356 0.04407 0.0660 0.0508 0.8936
13.500 0.7292 0.05504 0.04562 0.0665 0.0485 0.8975
13.750 0.7384 0.05658 0.04718 0.0668 0.0468 0.9018
14.000 0.7487 0.05804 0.04874 0.0672 0.0446 0.9059
14.250 0.7598 0.05939 0.05019 0.0676 0.0431 0.9103
14.500 0.7715 0.06078 0.05162 0.0678 0.0417 0.9154
14.750 0.7839 0.06214 0.05296 0.0679 0.0406 0.9207
15.000 0.7979 0.06344 0.05444 0.0681 0.0391 0.9263
15.250 0.8110 0.06489 0.05601 0.0680 0.0377 0.9331
15.500 0.8249 0.06640 0.05761 0.0676 0.0366 0.9400
15.750 0.8406 0.06787 0.05911 0.0669 0.0356 0.9480
16.000 0.8587 0.06947 0.06084 0.0659 0.0349 0.9562
16.250 0.8744 0.07147 0.06308 0.0647 0.0341 0.9663
16.500 0.8847 0.07333 0.06515 0.0639 0.0335 1.0000
16.750 0.8940 0.07571 0.06768 0.0633 0.0330 1.0000
17.000 0.9013 0.07831 0.07043 0.0625 0.0326 1.0000
17.250 0.9060 0.08118 0.07348 0.0617 0.0322 1.0000
17.500 0.9087 0.08432 0.07678 0.0608 0.0319 1.0000
17.750 0.9095 0.08764 0.08025 0.0597 0.0316 1.0000
18.000 0.9087 0.09121 0.08397 0.0584 0.0313 1.0000
18.250 0.9064 0.09501 0.08791 0.0570 0.0311 1.0000
18.500 0.9059 0.09860 0.09160 0.0555 0.0307 1.0000
18.750 0.8940 0.10381 0.09702 0.0533 0.0306 1.0000
19.000 0.8722 0.11068 0.10418 0.0500 0.0304 1.0000
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