NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 500,000 Max Cl/Cd: 71.43 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652215-il-500000-n5.txt Download as CSV file: xf-naca652215-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8538 0.09604 0.09309 -0.0417 1.0000 0.0126
-16.750 -0.9001 0.08247 0.07923 -0.0501 1.0000 0.0125
-16.500 -0.9194 0.07520 0.07178 -0.0544 1.0000 0.0126
-16.250 -0.9326 0.06947 0.06592 -0.0575 1.0000 0.0126
-16.000 -0.9374 0.06539 0.06175 -0.0596 1.0000 0.0128
-15.750 -0.9494 0.06055 0.05676 -0.0618 1.0000 0.0128
-15.500 -0.9571 0.05659 0.05265 -0.0632 1.0000 0.0129
-15.250 -0.9628 0.05310 0.04903 -0.0642 1.0000 0.0130
-15.000 -0.9632 0.05047 0.04631 -0.0649 1.0000 0.0132
-14.750 -0.9682 0.04735 0.04305 -0.0653 1.0000 0.0133
-14.500 -0.9698 0.04472 0.04029 -0.0654 1.0000 0.0134
-14.250 -0.9701 0.04230 0.03773 -0.0652 1.0000 0.0135
-14.000 -0.9677 0.04026 0.03558 -0.0650 1.0000 0.0138
-13.750 -0.9666 0.03802 0.03318 -0.0644 1.0000 0.0139
-13.500 -0.9624 0.03620 0.03123 -0.0638 1.0000 0.0142
-13.250 -0.9569 0.03451 0.02941 -0.0631 1.0000 0.0144
-13.000 -0.9495 0.03305 0.02782 -0.0623 1.0000 0.0147
-12.750 -0.9416 0.03161 0.02624 -0.0614 1.0000 0.0149
-12.500 -0.9322 0.03036 0.02487 -0.0604 1.0000 0.0151
-12.250 -0.9225 0.02909 0.02348 -0.0594 1.0000 0.0153
-12.000 -0.9133 0.02771 0.02203 -0.0582 1.0000 0.0156
-11.750 -0.9026 0.02664 0.02091 -0.0570 1.0000 0.0158
-11.500 -0.8729 0.02546 0.01966 -0.0596 0.9665 0.0161
-11.250 -0.8414 0.02438 0.01848 -0.0623 0.9500 0.0165
-11.000 -0.8163 0.02342 0.01741 -0.0635 0.9325 0.0168
-10.750 -0.7983 0.02278 0.01666 -0.0630 0.9150 0.0173
-10.500 -0.7833 0.02201 0.01578 -0.0618 0.9001 0.0175
-10.250 -0.7686 0.02134 0.01499 -0.0604 0.8868 0.0180
-10.000 -0.7538 0.02068 0.01421 -0.0590 0.8750 0.0183
-9.750 -0.7391 0.02002 0.01344 -0.0575 0.8646 0.0186
-9.500 -0.7242 0.01942 0.01273 -0.0560 0.8546 0.0189
-9.250 -0.7098 0.01879 0.01202 -0.0543 0.8453 0.0191
-9.000 -0.6992 0.01802 0.01118 -0.0521 0.8361 0.0195
-8.750 -0.6864 0.01747 0.01056 -0.0501 0.8277 0.0199
-8.500 -0.6702 0.01701 0.01003 -0.0485 0.8205 0.0203
-8.250 -0.6515 0.01656 0.00954 -0.0474 0.8133 0.0208
-8.000 -0.6323 0.01615 0.00906 -0.0463 0.8063 0.0215
-7.750 -0.6124 0.01573 0.00858 -0.0453 0.7997 0.0221
-7.500 -0.5923 0.01530 0.00809 -0.0444 0.7929 0.0227
-7.250 -0.5714 0.01491 0.00762 -0.0435 0.7873 0.0232
-7.000 -0.5496 0.01453 0.00718 -0.0428 0.7813 0.0237
-6.750 -0.5293 0.01404 0.00664 -0.0418 0.7756 0.0246
-6.500 -0.5069 0.01367 0.00624 -0.0412 0.7703 0.0256
-6.250 -0.4836 0.01335 0.00588 -0.0407 0.7645 0.0267
-6.000 -0.4598 0.01306 0.00553 -0.0403 0.7591 0.0279
-5.750 -0.4353 0.01280 0.00523 -0.0399 0.7542 0.0293
-5.500 -0.4114 0.01245 0.00487 -0.0395 0.7491 0.0317
-5.250 -0.3866 0.01219 0.00458 -0.0392 0.7443 0.0341
-5.000 -0.3615 0.01196 0.00429 -0.0390 0.7401 0.0372
-4.750 -0.3362 0.01168 0.00404 -0.0388 0.7354 0.0428
-4.500 -0.3111 0.01140 0.00379 -0.0386 0.7306 0.0536
-4.250 -0.2870 0.01102 0.00350 -0.0382 0.7261 0.0816
-4.000 -0.2638 0.01050 0.00320 -0.0379 0.7219 0.1360
-3.750 -0.2411 0.00988 0.00288 -0.0376 0.7175 0.2136
-3.500 -0.2198 0.00907 0.00250 -0.0371 0.7134 0.3255
-3.250 -0.1990 0.00820 0.00216 -0.0365 0.7096 0.4622
-3.000 -0.1732 0.00791 0.00209 -0.0364 0.7057 0.5295
-2.750 -0.1461 0.00779 0.00209 -0.0364 0.7015 0.5728
-2.500 -0.1187 0.00775 0.00212 -0.0364 0.6975 0.6066
-2.250 -0.0908 0.00777 0.00215 -0.0364 0.6941 0.6253
-2.000 -0.0620 0.00778 0.00212 -0.0367 0.6907 0.6345
-1.750 -0.0332 0.00776 0.00209 -0.0370 0.6870 0.6382
-1.500 -0.0044 0.00775 0.00205 -0.0373 0.6831 0.6417
-1.250 0.0244 0.00775 0.00201 -0.0376 0.6795 0.6452
-1.000 0.0533 0.00777 0.00197 -0.0379 0.6765 0.6488
-0.750 0.0822 0.00775 0.00197 -0.0382 0.6731 0.6517
-0.500 0.1110 0.00775 0.00196 -0.0385 0.6695 0.6549
-0.250 0.1398 0.00776 0.00196 -0.0388 0.6659 0.6584
0.000 0.1686 0.00778 0.00195 -0.0391 0.6628 0.6621
0.250 0.1976 0.00781 0.00196 -0.0395 0.6599 0.6653
0.500 0.2264 0.00780 0.00199 -0.0398 0.6564 0.6684
0.750 0.2551 0.00781 0.00202 -0.0400 0.6528 0.6720
1.000 0.2839 0.00784 0.00205 -0.0403 0.6496 0.6757
1.250 0.3127 0.00788 0.00208 -0.0406 0.6467 0.6793
1.500 0.3415 0.00790 0.00213 -0.0409 0.6436 0.6826
1.750 0.3701 0.00792 0.00220 -0.0412 0.6401 0.6862
2.000 0.3988 0.00794 0.00227 -0.0415 0.6367 0.6902
2.250 0.4275 0.00799 0.00233 -0.0418 0.6333 0.6942
2.500 0.4560 0.00804 0.00238 -0.0420 0.6291 0.6979
2.750 0.4841 0.00805 0.00246 -0.0422 0.6222 0.7014
3.000 0.5118 0.00809 0.00251 -0.0422 0.6132 0.7056
3.250 0.5389 0.00813 0.00255 -0.0421 0.5986 0.7101
3.500 0.5653 0.00819 0.00258 -0.0419 0.5752 0.7143
3.750 0.5900 0.00833 0.00265 -0.0414 0.5405 0.7183
4.000 0.6136 0.00859 0.00276 -0.0408 0.4955 0.7227
4.250 0.6319 0.00921 0.00304 -0.0393 0.4154 0.7274
4.500 0.6453 0.01021 0.00357 -0.0373 0.3126 0.7320
4.750 0.6603 0.01108 0.00409 -0.0355 0.2299 0.7371
5.000 0.6761 0.01188 0.00457 -0.0339 0.1605 0.7426
5.250 0.6926 0.01259 0.00503 -0.0323 0.1065 0.7476
5.500 0.7105 0.01316 0.00546 -0.0309 0.0717 0.7527
5.750 0.7296 0.01364 0.00586 -0.0297 0.0508 0.7582
6.000 0.7494 0.01406 0.00624 -0.0286 0.0402 0.7637
6.250 0.7693 0.01442 0.00662 -0.0275 0.0345 0.7695
6.500 0.7890 0.01479 0.00702 -0.0264 0.0310 0.7760
6.750 0.8077 0.01514 0.00741 -0.0250 0.0286 0.7821
7.000 0.8231 0.01554 0.00784 -0.0231 0.0266 0.7888
7.500 0.8552 0.01635 0.00879 -0.0196 0.0240 0.8025
7.750 0.8710 0.01682 0.00930 -0.0179 0.0230 0.8104
8.000 0.8852 0.01736 0.00989 -0.0161 0.0219 0.8184
8.250 0.8980 0.01802 0.01059 -0.0142 0.0210 0.8274
8.500 0.9131 0.01853 0.01120 -0.0126 0.0203 0.8361
8.750 0.9278 0.01911 0.01185 -0.0110 0.0197 0.8453
9.000 0.9414 0.01972 0.01255 -0.0093 0.0190 0.8555
9.250 0.9546 0.02037 0.01328 -0.0076 0.0186 0.8667
9.500 0.9670 0.02106 0.01405 -0.0059 0.0180 0.8798
9.750 0.9787 0.02179 0.01486 -0.0041 0.0177 0.8948
10.000 0.9882 0.02263 0.01579 -0.0021 0.0172 0.9140
10.250 0.9978 0.02365 0.01691 -0.0004 0.0168 0.9404
10.750 1.0323 0.02559 0.01900 -0.0002 0.0163 1.0000
11.000 1.0453 0.02663 0.02011 0.0008 0.0160 1.0000
11.250 1.0579 0.02772 0.02125 0.0017 0.0157 1.0000
11.500 1.0700 0.02885 0.02245 0.0026 0.0154 1.0000
11.750 1.0819 0.03003 0.02369 0.0035 0.0152 1.0000
12.000 1.0936 0.03124 0.02495 0.0043 0.0149 1.0000
12.250 1.1057 0.03243 0.02619 0.0050 0.0146 1.0000
12.500 1.1174 0.03367 0.02750 0.0057 0.0144 1.0000
12.750 1.1279 0.03502 0.02890 0.0064 0.0141 1.0000
13.000 1.1381 0.03642 0.03035 0.0070 0.0139 1.0000
13.250 1.1473 0.03794 0.03193 0.0077 0.0137 1.0000
13.500 1.1551 0.03963 0.03368 0.0083 0.0135 1.0000
13.750 1.1610 0.04158 0.03570 0.0091 0.0133 1.0000
14.000 1.1694 0.04329 0.03751 0.0095 0.0132 1.0000
14.250 1.1767 0.04515 0.03949 0.0100 0.0131 1.0000
14.500 1.1832 0.04713 0.04159 0.0103 0.0129 1.0000
14.750 1.1889 0.04925 0.04383 0.0106 0.0128 1.0000
15.000 1.1937 0.05151 0.04622 0.0108 0.0126 1.0000
15.250 1.1975 0.05393 0.04876 0.0108 0.0126 1.0000
15.500 1.1996 0.05661 0.05158 0.0107 0.0124 1.0000
15.750 1.2013 0.05940 0.05450 0.0105 0.0123 1.0000
16.000 1.2007 0.06259 0.05784 0.0101 0.0122 1.0000
16.250 1.2004 0.06580 0.06117 0.0094 0.0120 1.0000
16.500 1.1989 0.06926 0.06477 0.0085 0.0119 1.0000
16.750 1.1947 0.07323 0.06888 0.0074 0.0118 1.0000
17.000 1.1924 0.07705 0.07284 0.0060 0.0116 1.0000
17.250 1.1861 0.08162 0.07755 0.0043 0.0115 1.0000
17.500 1.1809 0.08617 0.08222 0.0023 0.0114 1.0000
17.750 1.1718 0.09157 0.08778 -0.0002 0.0113 1.0000
18.000 1.1592 0.09781 0.09420 -0.0032 0.0113 1.0000
18.250 1.1495 0.10375 0.10027 -0.0065 0.0112 1.0000
18.500 1.1337 0.11114 0.10783 -0.0106 0.0112 1.0000
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