AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 500,000 Max Cl/Cd: 103.18 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-9-il-500000.txt Download as CSV file: xf-ah21-9-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5610 0.06498 0.06282 -0.0334 1.0000 0.0154
-7.250 -0.5662 0.06069 0.05847 -0.0337 1.0000 0.0156
-7.000 -0.5640 0.05899 0.05675 -0.0325 1.0000 0.0162
-6.750 -0.5611 0.05506 0.05273 -0.0327 1.0000 0.0164
-6.500 -0.5548 0.05206 0.04964 -0.0324 1.0000 0.0170
-6.250 -0.5469 0.04824 0.04568 -0.0324 1.0000 0.0175
-6.000 -0.5271 0.04345 0.04067 -0.0346 0.9988 0.0184
-5.750 -0.4988 0.03842 0.03531 -0.0375 0.9966 0.0201
-5.500 -0.4622 0.03662 0.03309 -0.0388 0.9948 0.0223
-5.250 -0.4433 0.02794 0.02372 -0.0410 0.9924 0.0235
-5.000 -0.4171 0.02575 0.02144 -0.0421 0.9903 0.0253
-4.750 -0.3870 0.02138 0.01645 -0.0419 0.9888 0.0206
-4.500 -0.3563 0.01933 0.01405 -0.0425 0.9872 0.0213
-4.250 -0.3254 0.01713 0.01150 -0.0430 0.9860 0.0213
-4.000 -0.2938 0.01561 0.00974 -0.0437 0.9850 0.0217
-3.750 -0.2602 0.01487 0.00886 -0.0449 0.9838 0.0223
-3.500 -0.2298 0.01304 0.00686 -0.0455 0.9832 0.0240
-3.250 -0.2030 0.01219 0.00595 -0.0454 0.9803 0.0253
-3.000 -0.1731 0.01163 0.00535 -0.0459 0.9775 0.0267
-2.750 -0.1408 0.01121 0.00488 -0.0469 0.9752 0.0283
-2.500 -0.1068 0.01090 0.00453 -0.0483 0.9732 0.0310
-2.250 -0.0715 0.01056 0.00412 -0.0499 0.9717 0.0342
-2.000 -0.0356 0.01011 0.00381 -0.0517 0.9704 0.0726
-1.750 -0.0112 0.00908 0.00365 -0.0517 0.9663 0.3090
-1.500 0.0172 0.00823 0.00359 -0.0524 0.9629 0.5407
-1.250 0.0469 0.00759 0.00364 -0.0528 0.9603 0.7316
-1.000 0.0791 0.00729 0.00365 -0.0533 0.9582 0.8308
-0.750 0.1124 0.00711 0.00365 -0.0539 0.9565 0.9067
-0.500 0.1558 0.00703 0.00365 -0.0567 0.9548 0.9757
-0.250 0.2068 0.00693 0.00353 -0.0617 0.9534 0.9925
0.000 0.2498 0.00679 0.00336 -0.0649 0.9497 1.0000
0.250 0.2942 0.00656 0.00312 -0.0682 0.9468 1.0000
0.500 0.3435 0.00629 0.00285 -0.0726 0.9444 1.0000
0.750 0.3739 0.00606 0.00261 -0.0729 0.9359 1.0000
1.000 0.4160 0.00577 0.00233 -0.0757 0.9296 1.0000
1.250 0.4427 0.00558 0.00215 -0.0751 0.9168 1.0000
1.500 0.4720 0.00542 0.00198 -0.0752 0.9014 1.0000
1.750 0.4996 0.00531 0.00185 -0.0748 0.8770 1.0000
2.000 0.5287 0.00527 0.00175 -0.0748 0.8466 1.0000
2.250 0.5541 0.00537 0.00168 -0.0739 0.7948 1.0000
2.500 0.5730 0.00567 0.00169 -0.0717 0.7246 1.0000
2.750 0.5857 0.00623 0.00180 -0.0683 0.6259 1.0000
3.000 0.5973 0.00699 0.00203 -0.0649 0.5036 1.0000
3.250 0.6120 0.00781 0.00230 -0.0625 0.3789 1.0000
3.500 0.6295 0.00863 0.00261 -0.0607 0.2636 1.0000
3.750 0.6497 0.00933 0.00292 -0.0595 0.1783 1.0000
4.000 0.6713 0.00994 0.00323 -0.0585 0.1186 1.0000
4.250 0.6940 0.01046 0.00359 -0.0576 0.0824 1.0000
4.500 0.7175 0.01091 0.00396 -0.0568 0.0616 1.0000
4.750 0.7409 0.01141 0.00440 -0.0560 0.0478 1.0000
5.000 0.7643 0.01191 0.00492 -0.0551 0.0392 1.0000
5.250 0.7852 0.01278 0.00581 -0.0538 0.0323 1.0000
5.500 0.8094 0.01318 0.00629 -0.0531 0.0304 1.0000
5.750 0.8326 0.01376 0.00693 -0.0522 0.0282 1.0000
6.000 0.8559 0.01430 0.00751 -0.0514 0.0258 1.0000
6.250 0.8752 0.01562 0.00891 -0.0498 0.0232 1.0000
6.500 0.8970 0.01677 0.01018 -0.0487 0.0221 1.0000
6.750 0.9210 0.01737 0.01089 -0.0480 0.0208 1.0000
7.000 0.9445 0.01796 0.01156 -0.0473 0.0190 1.0000
7.250 0.9674 0.01870 0.01237 -0.0465 0.0176 1.0000
7.500 0.9883 0.02009 0.01386 -0.0454 0.0162 1.0000
7.750 1.0062 0.02313 0.01726 -0.0438 0.0149 1.0000
8.000 1.0286 0.02369 0.01797 -0.0429 0.0139 1.0000
8.250 1.0493 0.02469 0.01916 -0.0418 0.0127 1.0000
8.500 1.0684 0.02592 0.02056 -0.0405 0.0118 1.0000
8.750 1.0863 0.02720 0.02199 -0.0392 0.0112 1.0000
9.000 1.0994 0.02944 0.02445 -0.0373 0.0107 1.0000
9.250 1.0915 0.03562 0.03129 -0.0328 0.0102 1.0000
9.500 1.0812 0.04086 0.03706 -0.0284 0.0101 1.0000
9.750 1.0796 0.04386 0.04041 -0.0252 0.0099 1.0000
10.000 1.0641 0.04813 0.04501 -0.0209 0.0099 1.0000
10.250 1.0384 0.05224 0.04937 -0.0159 0.0100 1.0000
10.500 0.9714 0.06555 0.06327 -0.0120 0.0118 1.0000
10.750 0.9555 0.06952 0.06734 -0.0127 0.0115 1.0000
11.000 0.9367 0.07530 0.07323 -0.0160 0.0114 1.0000
11.250 0.9384 0.07737 0.07532 -0.0184 0.0111 1.0000
11.500 0.9354 0.08236 0.08037 -0.0236 0.0108 1.0000
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Polar data table (+)
Polar graphs
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