AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 50,000 Max Cl/Cd: 35.56 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-7-il-50000-n5.txt Download as CSV file: xf-ah21-7-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH21 7% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3864 0.11015 0.10313 -0.0350 1.0000 0.0718
-10.000 -0.4733 0.11505 0.10763 -0.0327 1.0000 0.0882
-9.750 -0.4812 0.10752 0.10010 -0.0365 1.0000 0.0592
-9.500 -0.4797 0.10405 0.09667 -0.0362 1.0000 0.0586
-9.250 -0.4830 0.10042 0.09311 -0.0367 1.0000 0.0584
-9.000 -0.4857 0.09693 0.08968 -0.0367 1.0000 0.0578
-8.750 -0.4922 0.09331 0.08615 -0.0372 1.0000 0.0576
-8.500 -0.5000 0.08979 0.08273 -0.0374 1.0000 0.0571
-8.250 -0.5121 0.08617 0.07919 -0.0377 1.0000 0.0568
-8.000 -0.5219 0.08226 0.07536 -0.0384 1.0000 0.0559
-7.750 -0.5310 0.07793 0.07106 -0.0393 1.0000 0.0552
-7.500 -0.5394 0.07355 0.06666 -0.0399 1.0000 0.0546
-7.250 -0.5458 0.06914 0.06219 -0.0403 1.0000 0.0540
-7.000 -0.5498 0.06464 0.05755 -0.0406 1.0000 0.0532
-6.750 -0.5509 0.06001 0.05271 -0.0408 1.0000 0.0524
-6.500 -0.5482 0.05543 0.04782 -0.0408 1.0000 0.0517
-6.250 -0.5412 0.05114 0.04314 -0.0406 1.0000 0.0512
-6.000 -0.5304 0.04720 0.03878 -0.0403 1.0000 0.0510
-5.750 -0.5163 0.04366 0.03478 -0.0398 1.0000 0.0512
-5.500 -0.4995 0.04053 0.03118 -0.0392 1.0000 0.0515
-5.250 -0.4809 0.03800 0.02825 -0.0386 1.0000 0.0532
-5.000 -0.4605 0.03573 0.02552 -0.0379 1.0000 0.0560
-4.750 -0.4385 0.03358 0.02281 -0.0371 1.0000 0.0581
-4.500 -0.4153 0.03164 0.02039 -0.0362 1.0000 0.0594
-4.250 -0.3926 0.02987 0.01845 -0.0354 1.0000 0.0612
-4.000 -0.3700 0.02850 0.01696 -0.0345 1.0000 0.0637
-3.750 -0.3473 0.02735 0.01565 -0.0334 1.0000 0.0679
-3.500 -0.3246 0.02636 0.01444 -0.0324 1.0000 0.0744
-3.250 -0.3023 0.02544 0.01348 -0.0314 1.0000 0.0824
-3.000 -0.2793 0.02450 0.01246 -0.0305 1.0000 0.0926
-2.750 -0.2560 0.02361 0.01159 -0.0299 1.0000 0.1169
-2.500 -0.2323 0.02242 0.01080 -0.0298 1.0000 0.1797
-2.250 -0.2111 0.02065 0.01042 -0.0295 1.0000 0.4183
-2.000 -0.2003 0.01974 0.01060 -0.0250 1.0000 0.6631
-1.750 -0.1832 0.01939 0.01072 -0.0205 1.0000 0.8861
-1.500 -0.1434 0.01922 0.01022 -0.0233 1.0000 1.0000
-1.250 -0.1226 0.01931 0.00996 -0.0227 1.0000 1.0000
-1.000 -0.1016 0.01944 0.00980 -0.0221 1.0000 1.0000
-0.750 -0.0804 0.01960 0.00971 -0.0215 1.0000 1.0000
-0.500 -0.0591 0.01980 0.00967 -0.0209 1.0000 1.0000
-0.250 -0.0379 0.02004 0.00971 -0.0204 1.0000 1.0000
0.000 -0.0146 0.02033 0.00982 -0.0203 0.9991 1.0000
0.250 0.0222 0.02086 0.01019 -0.0228 0.9922 1.0000
0.500 0.0589 0.02141 0.01057 -0.0253 0.9851 1.0000
0.750 0.0940 0.02187 0.01092 -0.0274 0.9772 1.0000
1.000 0.1316 0.02242 0.01138 -0.0300 0.9698 1.0000
1.250 0.1661 0.02283 0.01173 -0.0319 0.9606 1.0000
1.500 0.2007 0.02324 0.01211 -0.0338 0.9512 1.0000
1.750 0.2389 0.02370 0.01255 -0.0364 0.9424 1.0000
2.000 0.2741 0.02403 0.01290 -0.0382 0.9316 1.0000
2.250 0.3080 0.02431 0.01322 -0.0398 0.9198 1.0000
2.500 0.3430 0.02455 0.01353 -0.0414 0.9075 1.0000
2.750 0.3784 0.02472 0.01378 -0.0430 0.8943 1.0000
3.000 0.4144 0.02480 0.01398 -0.0445 0.8800 1.0000
3.250 0.4509 0.02477 0.01410 -0.0459 0.8643 1.0000
3.500 0.4894 0.02458 0.01407 -0.0473 0.8476 1.0000
3.750 0.5248 0.02427 0.01394 -0.0480 0.8279 1.0000
4.000 0.5606 0.02378 0.01367 -0.0483 0.8058 1.0000
4.250 0.5939 0.02318 0.01328 -0.0479 0.7803 1.0000
4.500 0.6275 0.02251 0.01280 -0.0473 0.7494 1.0000
4.750 0.6609 0.02188 0.01238 -0.0466 0.7085 1.0000
5.000 0.7017 0.02117 0.01175 -0.0467 0.6464 1.0000
5.250 0.7454 0.02096 0.01119 -0.0474 0.5393 1.0000
5.500 0.7667 0.02179 0.01140 -0.0453 0.4279 1.0000
5.750 0.7793 0.02302 0.01211 -0.0426 0.3385 1.0000
6.000 0.7923 0.02435 0.01300 -0.0403 0.2694 1.0000
6.250 0.8074 0.02572 0.01403 -0.0386 0.2194 1.0000
6.500 0.8258 0.02705 0.01517 -0.0374 0.1831 1.0000
6.750 0.8459 0.02838 0.01638 -0.0364 0.1567 1.0000
7.000 0.8689 0.02974 0.01775 -0.0358 0.1371 1.0000
7.250 0.8924 0.03109 0.01908 -0.0354 0.1211 1.0000
7.500 0.9202 0.03260 0.02071 -0.0354 0.1094 1.0000
7.750 0.9464 0.03416 0.02239 -0.0352 0.0988 1.0000
8.000 0.9723 0.03589 0.02415 -0.0352 0.0912 1.0000
8.250 1.0004 0.03794 0.02656 -0.0351 0.0848 1.0000
8.500 1.0230 0.03981 0.02839 -0.0348 0.0791 1.0000
8.750 1.0433 0.04213 0.03124 -0.0337 0.0742 1.0000
9.000 1.0626 0.04470 0.03417 -0.0327 0.0709 1.0000
9.250 1.0791 0.04695 0.03656 -0.0316 0.0676 1.0000
9.500 1.0893 0.04976 0.03979 -0.0296 0.0646 1.0000
9.750 1.0931 0.05288 0.04346 -0.0269 0.0621 1.0000
10.000 1.0942 0.05625 0.04728 -0.0242 0.0606 1.0000
10.250 1.0910 0.05971 0.05113 -0.0213 0.0596 1.0000
10.500 1.0830 0.06314 0.05489 -0.0183 0.0588 1.0000
10.750 1.0709 0.06643 0.05846 -0.0151 0.0581 1.0000
11.000 1.0570 0.06982 0.06207 -0.0123 0.0574 1.0000
11.250 1.0381 0.07372 0.06620 -0.0103 0.0571 1.0000
11.500 1.0115 0.07865 0.07136 -0.0093 0.0573 1.0000
11.750 0.9745 0.08554 0.07848 -0.0108 0.0585 1.0000
12.000 0.9370 0.09429 0.08735 -0.0153 0.0598 1.0000
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Polar data table (+)
Polar graphs
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