AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 50,000 Max Cl/Cd: 34.22 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-9-il-50000.txt Download as CSV file: xf-ah21-9-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4849 0.09508 0.08822 -0.0094 1.0000 0.2857
-7.500 -0.4843 0.09224 0.08546 -0.0080 1.0000 0.3006
-7.250 -0.4852 0.08962 0.08291 -0.0063 1.0000 0.3169
-7.000 -0.4932 0.08754 0.08095 -0.0042 1.0000 0.3338
-6.750 -0.5105 0.08607 0.07964 -0.0020 1.0000 0.3499
-6.500 -0.4889 0.08185 0.07540 0.0009 1.0000 0.3750
-6.250 -0.4832 0.07880 0.07241 0.0037 1.0000 0.3988
-6.000 -0.4791 0.07605 0.06972 0.0071 1.0000 0.4282
-5.750 -0.4875 0.07441 0.06819 0.0113 1.0000 0.4624
-5.000 -0.4766 0.05174 0.04474 -0.0301 1.0000 0.2135
-4.750 -0.4386 0.04300 0.03458 -0.0373 1.0000 0.1375
-4.500 -0.4165 0.03911 0.03030 -0.0372 1.0000 0.1312
-4.250 -0.3895 0.03594 0.02611 -0.0373 1.0000 0.1254
-4.000 -0.3651 0.03287 0.02273 -0.0368 1.0000 0.1235
-3.750 -0.3392 0.03022 0.01964 -0.0361 1.0000 0.1220
-3.500 -0.3125 0.02801 0.01694 -0.0353 1.0000 0.1224
-3.250 -0.2858 0.02618 0.01468 -0.0343 1.0000 0.1261
-3.000 -0.2609 0.02463 0.01305 -0.0334 1.0000 0.1383
-2.750 -0.2354 0.02309 0.01148 -0.0321 1.0000 0.1509
-2.500 -0.2099 0.02162 0.01006 -0.0309 1.0000 0.1734
-2.250 -0.1719 0.01658 0.00860 -0.0279 1.0000 1.0000
-2.000 -0.1513 0.01652 0.00786 -0.0267 1.0000 1.0000
-1.750 -0.1303 0.01649 0.00737 -0.0257 1.0000 1.0000
-1.500 -0.1088 0.01650 0.00699 -0.0249 1.0000 1.0000
-1.250 -0.0870 0.01654 0.00671 -0.0241 1.0000 1.0000
-1.000 -0.0649 0.01660 0.00646 -0.0234 1.0000 1.0000
-0.750 -0.0428 0.01670 0.00631 -0.0227 1.0000 1.0000
-0.500 -0.0206 0.01681 0.00622 -0.0220 1.0000 1.0000
-0.250 0.0016 0.01695 0.00619 -0.0214 1.0000 1.0000
0.000 0.0238 0.01711 0.00620 -0.0208 1.0000 1.0000
0.250 0.0459 0.01730 0.00624 -0.0201 1.0000 1.0000
0.500 0.0678 0.01751 0.00635 -0.0195 1.0000 1.0000
0.750 0.0897 0.01775 0.00652 -0.0189 1.0000 1.0000
1.000 0.1113 0.01801 0.00673 -0.0184 1.0000 1.0000
1.250 0.1328 0.01831 0.00699 -0.0178 1.0000 1.0000
1.500 0.1540 0.01863 0.00730 -0.0172 1.0000 1.0000
1.750 0.1750 0.01899 0.00766 -0.0167 1.0000 1.0000
2.000 0.1956 0.01938 0.00808 -0.0162 1.0000 1.0000
2.250 0.2159 0.01981 0.00857 -0.0157 1.0000 1.0000
2.500 0.2358 0.02029 0.00913 -0.0152 1.0000 1.0000
2.750 0.2552 0.02083 0.00975 -0.0147 1.0000 1.0000
3.000 0.2742 0.02142 0.01045 -0.0143 1.0000 1.0000
3.250 0.2924 0.02208 0.01123 -0.0140 1.0000 1.0000
3.500 0.3100 0.02283 0.01211 -0.0137 1.0000 1.0000
3.750 0.3268 0.02367 0.01315 -0.0135 1.0000 1.0000
4.000 0.3425 0.02463 0.01428 -0.0134 1.0000 1.0000
4.250 0.4241 0.02647 0.01666 -0.0254 0.9627 1.0000
4.500 0.5577 0.02542 0.01671 -0.0411 0.8828 1.0000
4.750 0.6871 0.02008 0.01062 -0.0410 0.4241 1.0000
5.000 0.7028 0.02377 0.01263 -0.0384 0.2562 1.0000
5.250 0.7363 0.02631 0.01477 -0.0388 0.1951 1.0000
5.500 0.7705 0.02882 0.01714 -0.0392 0.1650 1.0000
5.750 0.8006 0.03140 0.01983 -0.0390 0.1470 1.0000
6.000 0.8293 0.03417 0.02291 -0.0385 0.1371 1.0000
6.250 0.8513 0.03680 0.02603 -0.0370 0.1272 1.0000
6.500 0.8753 0.04030 0.02961 -0.0364 0.1217 1.0000
6.750 0.8940 0.04387 0.03381 -0.0344 0.1210 1.0000
7.000 0.9104 0.04792 0.03836 -0.0326 0.1215 1.0000
7.250 0.9216 0.05192 0.04293 -0.0303 0.1213 1.0000
7.500 0.9294 0.05602 0.04756 -0.0281 0.1210 1.0000
7.750 0.9249 0.06092 0.05332 -0.0254 0.1279 1.0000
8.000 0.9302 0.06640 0.05905 -0.0242 0.1338 1.0000
8.250 0.9156 0.07304 0.06628 -0.0237 0.1525 1.0000
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Polar data table (+)
Polar graphs
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