AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 100,000 Max Cl/Cd: 51.59 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-7-il-100000-n5.txt Download as CSV file: xf-ah21-7-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4944 0.09047 0.08539 -0.0360 1.0000 0.0349
-8.750 -0.5021 0.08691 0.08190 -0.0361 1.0000 0.0343
-8.500 -0.5132 0.08331 0.07837 -0.0362 1.0000 0.0338
-8.250 -0.5304 0.07959 0.07474 -0.0362 1.0000 0.0334
-8.000 -0.5459 0.07520 0.07040 -0.0376 1.0000 0.0328
-7.750 -0.5590 0.06993 0.06513 -0.0390 1.0000 0.0321
-7.500 -0.5707 0.06435 0.05946 -0.0400 1.0000 0.0314
-7.250 -0.5800 0.05833 0.05323 -0.0406 1.0000 0.0306
-7.000 -0.5849 0.05212 0.04666 -0.0407 1.0000 0.0298
-6.750 -0.5840 0.04624 0.04027 -0.0404 1.0000 0.0293
-6.500 -0.5757 0.04188 0.03543 -0.0398 1.0000 0.0292
-6.250 -0.5630 0.03845 0.03157 -0.0390 1.0000 0.0294
-6.000 -0.5471 0.03578 0.02853 -0.0382 1.0000 0.0298
-5.750 -0.5294 0.03403 0.02656 -0.0375 1.0000 0.0313
-5.500 -0.5100 0.03196 0.02411 -0.0368 1.0000 0.0327
-5.250 -0.4889 0.02975 0.02145 -0.0361 1.0000 0.0335
-5.000 -0.4666 0.02776 0.01904 -0.0353 1.0000 0.0340
-4.750 -0.4416 0.02608 0.01698 -0.0350 0.9994 0.0347
-4.500 -0.4113 0.02461 0.01519 -0.0356 0.9973 0.0356
-4.250 -0.3805 0.02350 0.01382 -0.0362 0.9950 0.0367
-4.000 -0.3515 0.02241 0.01275 -0.0370 0.9927 0.0396
-3.750 -0.3219 0.02166 0.01195 -0.0377 0.9898 0.0429
-3.500 -0.2915 0.02092 0.01107 -0.0383 0.9870 0.0454
-3.250 -0.2602 0.02022 0.01029 -0.0393 0.9844 0.0488
-3.000 -0.2304 0.01964 0.00967 -0.0399 0.9813 0.0552
-2.750 -0.2009 0.01908 0.00910 -0.0405 0.9776 0.0712
-2.500 -0.1702 0.01843 0.00870 -0.0415 0.9744 0.1159
-2.250 -0.1397 0.01751 0.00856 -0.0430 0.9718 0.2707
-2.000 -0.1153 0.01651 0.00863 -0.0428 0.9683 0.5117
-1.750 -0.0921 0.01608 0.00875 -0.0414 0.9637 0.6696
-1.500 -0.0676 0.01595 0.00896 -0.0397 0.9597 0.7996
-1.250 -0.0329 0.01598 0.00908 -0.0401 0.9570 0.9079
-1.000 0.0199 0.01595 0.00891 -0.0453 0.9546 1.0000
-0.750 0.0497 0.01601 0.00881 -0.0461 0.9486 1.0000
-0.500 0.0855 0.01614 0.00878 -0.0481 0.9446 1.0000
-0.250 0.1122 0.01618 0.00870 -0.0481 0.9374 1.0000
0.000 0.1465 0.01628 0.00869 -0.0497 0.9323 1.0000
0.250 0.1766 0.01634 0.00867 -0.0504 0.9258 1.0000
0.500 0.2090 0.01640 0.00866 -0.0514 0.9193 1.0000
0.750 0.2416 0.01644 0.00865 -0.0525 0.9129 1.0000
1.000 0.2731 0.01645 0.00863 -0.0533 0.9053 1.0000
1.250 0.3046 0.01644 0.00861 -0.0540 0.8975 1.0000
1.500 0.3399 0.01636 0.00853 -0.0554 0.8900 1.0000
1.750 0.3692 0.01629 0.00847 -0.0555 0.8798 1.0000
2.000 0.4059 0.01608 0.00831 -0.0569 0.8714 1.0000
2.250 0.4405 0.01581 0.00809 -0.0578 0.8609 1.0000
2.500 0.4712 0.01553 0.00786 -0.0578 0.8479 1.0000
2.750 0.5033 0.01520 0.00760 -0.0580 0.8335 1.0000
3.000 0.5371 0.01484 0.00731 -0.0584 0.8173 1.0000
3.250 0.5644 0.01461 0.00715 -0.0577 0.7945 1.0000
3.500 0.5994 0.01429 0.00690 -0.0583 0.7679 1.0000
3.750 0.6422 0.01393 0.00655 -0.0603 0.7287 1.0000
4.000 0.6887 0.01373 0.00619 -0.0629 0.6604 1.0000
4.250 0.7248 0.01405 0.00611 -0.0638 0.5627 1.0000
4.500 0.7453 0.01477 0.00633 -0.0621 0.4651 1.0000
4.750 0.7611 0.01563 0.00672 -0.0598 0.3770 1.0000
5.000 0.7769 0.01652 0.00720 -0.0578 0.3002 1.0000
5.250 0.7940 0.01738 0.00776 -0.0560 0.2389 1.0000
5.500 0.8120 0.01824 0.00835 -0.0545 0.1910 1.0000
5.750 0.8310 0.01904 0.00899 -0.0531 0.1566 1.0000
6.000 0.8498 0.01986 0.00967 -0.0517 0.1310 1.0000
6.250 0.8690 0.02065 0.01042 -0.0504 0.1124 1.0000
6.500 0.8879 0.02148 0.01125 -0.0489 0.0988 1.0000
6.750 0.9066 0.02234 0.01210 -0.0475 0.0879 1.0000
7.000 0.9246 0.02327 0.01300 -0.0460 0.0796 1.0000
7.250 0.9440 0.02420 0.01404 -0.0446 0.0731 1.0000
7.500 0.9621 0.02520 0.01503 -0.0433 0.0673 1.0000
7.750 0.9821 0.02623 0.01622 -0.0421 0.0620 1.0000
8.000 1.0020 0.02736 0.01744 -0.0409 0.0580 1.0000
8.250 1.0210 0.02870 0.01876 -0.0399 0.0546 1.0000
8.500 1.0425 0.02995 0.02024 -0.0389 0.0510 1.0000
8.750 1.0630 0.03128 0.02174 -0.0380 0.0478 1.0000
9.000 1.0830 0.03275 0.02335 -0.0371 0.0456 1.0000
9.250 1.1029 0.03463 0.02527 -0.0364 0.0435 1.0000
9.500 1.1209 0.03646 0.02745 -0.0350 0.0413 1.0000
9.750 1.1361 0.03827 0.02962 -0.0334 0.0390 1.0000
10.000 1.1495 0.04035 0.03199 -0.0317 0.0373 1.0000
10.250 1.1605 0.04244 0.03434 -0.0297 0.0361 1.0000
10.500 1.1695 0.04438 0.03646 -0.0277 0.0349 1.0000
10.750 1.1763 0.04685 0.03904 -0.0257 0.0336 1.0000
11.000 1.1708 0.04932 0.04196 -0.0217 0.0327 1.0000
11.250 1.1622 0.05213 0.04519 -0.0179 0.0319 1.0000
11.500 1.1499 0.05526 0.04869 -0.0143 0.0312 1.0000
11.750 1.1343 0.05877 0.05253 -0.0113 0.0308 1.0000
12.000 1.1156 0.06269 0.05676 -0.0089 0.0305 1.0000
12.250 1.0940 0.06717 0.06152 -0.0076 0.0304 1.0000
12.500 1.0696 0.07239 0.06699 -0.0077 0.0304 1.0000
12.750 1.0420 0.07875 0.07358 -0.0096 0.0306 1.0000
13.000 1.0122 0.08664 0.08163 -0.0138 0.0309 1.0000
13.250 0.9785 0.09721 0.09235 -0.0210 0.0315 1.0000
13.500 0.9438 0.11070 0.10590 -0.0303 0.0323 1.0000
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Polar data table (+)
Polar graphs
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