AH 93-W-215 (ah93w215-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-215 (ah93w215-il) Reynolds number: 50,000 Max Cl/Cd: 2.68 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w215-il-50000.txt Download as CSV file: xf-ah93w215-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-215
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2250 0.12524 0.11854 -0.0437 0.9586 0.4040
-9.500 -0.5059 0.08389 0.07722 -0.0659 0.9568 0.2328
-9.250 -0.5592 0.07779 0.07109 -0.0651 0.9492 0.2306
-9.000 -0.6289 0.07221 0.06538 -0.0617 0.9431 0.2272
-8.750 -0.6884 0.06840 0.06139 -0.0555 0.9375 0.2250
-8.500 -0.7255 0.06498 0.05772 -0.0510 0.9329 0.2251
-8.250 -0.7438 0.06178 0.05420 -0.0482 0.9287 0.2274
-8.000 -0.7614 0.05907 0.05111 -0.0446 0.9250 0.2303
-7.750 -0.7811 0.05682 0.04844 -0.0399 0.9217 0.2328
-7.500 -0.7715 0.05550 0.04716 -0.0383 0.9185 0.2380
-7.250 -0.7614 0.05440 0.04598 -0.0368 0.9154 0.2446
-7.000 -0.7621 0.05258 0.04369 -0.0343 0.9128 0.2509
-6.750 -0.7367 0.05167 0.04287 -0.0349 0.9088 0.2597
-6.500 -0.7368 0.05063 0.04162 -0.0317 0.9070 0.2668
-6.250 -0.7317 0.04965 0.04053 -0.0293 0.9061 0.2741
-6.000 -0.7229 0.04904 0.03991 -0.0272 0.9048 0.2832
-5.750 -0.7156 0.04821 0.03896 -0.0250 0.9038 0.2928
-5.500 -0.7060 0.04773 0.03844 -0.0230 0.9031 0.3042
-5.250 -0.6958 0.04727 0.03804 -0.0211 0.9037 0.3157
-5.000 -0.8493 0.04380 0.03435 0.0072 1.0000 0.2899
-4.750 -0.8341 0.04323 0.03396 0.0084 1.0000 0.3015
-4.500 -0.8203 0.04254 0.03327 0.0098 1.0000 0.3146
-4.250 -0.8068 0.04192 0.03261 0.0111 1.0000 0.3299
-4.000 -0.7931 0.04145 0.03215 0.0126 1.0000 0.3473
-3.750 -0.7790 0.04109 0.03193 0.0141 1.0000 0.3668
-3.500 -0.7652 0.04089 0.03193 0.0157 1.0000 0.3887
-3.250 -0.7518 0.04081 0.03205 0.0175 1.0000 0.4138
-3.000 -0.7396 0.04076 0.03215 0.0195 1.0000 0.4450
-2.750 -0.7276 0.04094 0.03255 0.0219 1.0000 0.4800
-2.500 -0.7163 0.04131 0.03316 0.0246 1.0000 0.5184
-2.250 -0.7057 0.04181 0.03387 0.0277 1.0000 0.5597
-2.000 -0.6952 0.04249 0.03473 0.0311 1.0000 0.5992
-1.750 -0.6848 0.04330 0.03567 0.0347 1.0000 0.6356
-1.500 -0.6752 0.04406 0.03648 0.0383 1.0000 0.6703
-1.250 -0.6617 0.04520 0.03766 0.0414 0.9985 0.7030
-1.000 -0.6383 0.04744 0.03990 0.0430 0.9932 0.7361
-0.750 -0.6186 0.04882 0.04123 0.0446 0.9860 0.7668
-0.500 -0.5947 0.05057 0.04293 0.0456 0.9786 0.7957
-0.250 -0.5623 0.05294 0.04522 0.0449 0.9698 0.8252
0.000 -0.5359 0.05406 0.04626 0.0447 0.9593 0.8526
0.250 -0.4914 0.05625 0.04836 0.0411 0.9497 0.8770
0.500 -0.4273 0.05987 0.05183 0.0334 0.9412 0.9021
0.750 -0.3511 0.06340 0.05522 0.0227 0.9291 0.9230
1.000 -0.2657 0.06724 0.05892 0.0098 0.9179 0.9393
1.250 -0.1752 0.07176 0.06328 -0.0047 0.9084 0.9563
1.500 -0.1101 0.07414 0.06555 -0.0148 0.8937 0.9705
1.750 -0.0599 0.07589 0.06723 -0.0224 0.8799 0.9830
2.000 0.0124 0.07970 0.07093 -0.0344 0.8713 0.9974
2.250 0.0240 0.07954 0.07070 -0.0349 0.8560 1.0000
2.500 0.0195 0.07919 0.07028 -0.0324 0.8439 1.0000
2.750 0.0361 0.08037 0.07135 -0.0333 0.8336 1.0000
3.000 0.0216 0.07902 0.06995 -0.0290 0.8194 1.0000
3.250 0.0402 0.08102 0.07182 -0.0299 0.8121 1.0000
3.500 0.0144 0.07848 0.06923 -0.0237 0.7976 1.0000
3.750 0.0304 0.08065 0.07125 -0.0238 0.7914 1.0000
4.000 0.0066 0.07806 0.06859 -0.0177 0.7766 1.0000
4.250 0.0313 0.08097 0.07132 -0.0189 0.7706 1.0000
4.500 0.0205 0.07948 0.06975 -0.0150 0.7564 1.0000
4.750 0.0557 0.08332 0.07344 -0.0176 0.7507 1.0000
5.000 0.0421 0.08177 0.07182 -0.0136 0.7375 1.0000
5.250 0.0771 0.08531 0.07525 -0.0160 0.7309 1.0000
5.500 0.0673 0.08459 0.07447 -0.0128 0.7194 1.0000
5.750 0.0966 0.08739 0.07717 -0.0144 0.7117 1.0000
6.000 0.0965 0.08805 0.07778 -0.0127 0.7033 1.0000
6.250 0.1173 0.08993 0.07960 -0.0132 0.6930 1.0000
6.500 0.1524 0.09441 0.08399 -0.0157 0.6885 1.0000
6.750 0.1374 0.09287 0.08244 -0.0123 0.6763 1.0000
7.000 0.1712 0.09652 0.08603 -0.0143 0.6697 1.0000
7.250 0.1636 0.09660 0.08609 -0.0122 0.6611 1.0000
7.500 0.1840 0.09875 0.08820 -0.0128 0.6523 1.0000
8.000 0.2024 0.10207 0.09148 -0.0122 0.6367 1.0000
8.250 0.2324 0.10546 0.09484 -0.0137 0.6296 1.0000
8.500 0.2345 0.10701 0.09638 -0.0131 0.6243 1.0000
8.750 0.2435 0.10819 0.09756 -0.0127 0.6136 1.0000
9.000 0.2813 0.11307 0.10243 -0.0151 0.6082 1.0000
9.250 0.2640 0.11225 0.10160 -0.0128 0.5999 1.0000
9.500 0.2850 0.11482 0.10418 -0.0135 0.5918 1.0000
9.750 0.3158 0.11972 0.10907 -0.0155 0.5877 1.0000
10.000 0.3000 0.11850 0.10787 -0.0134 0.5771 1.0000
10.250 0.3275 0.12212 0.11150 -0.0148 0.5708 1.0000
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Polar data table (+)
Polar graphs
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