AH 83-159 (ah83159-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-159 (ah83159-il) Reynolds number: 100,000 Max Cl/Cd: 28.99 at α=11° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83159-il-100000-n5.txt Download as CSV file: xf-ah83159-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-159
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1209 0.12314 0.11811 -0.0803 0.8514 0.0518
-12.750 -0.1156 0.12014 0.11510 -0.0814 0.8486 0.0527
-12.500 -0.2085 0.12299 0.11768 -0.0899 0.8720 0.0494
-12.250 -0.1894 0.11938 0.11403 -0.0886 0.8680 0.0508
-12.000 -0.1804 0.11612 0.11076 -0.0894 0.8640 0.0519
-11.750 -0.1750 0.11269 0.10731 -0.0909 0.8605 0.0524
-11.500 -0.1720 0.10892 0.10354 -0.0927 0.8571 0.0524
-11.250 -0.1736 0.10469 0.09935 -0.0952 0.8529 0.0514
-11.000 -0.1869 0.09402 0.08866 -0.1007 0.8494 0.0281
-10.750 -0.1820 0.09091 0.08554 -0.1014 0.8459 0.0276
-10.500 -0.1806 0.08715 0.08178 -0.1029 0.8426 0.0271
-10.250 -0.1818 0.08304 0.07771 -0.1049 0.8385 0.0266
-10.000 -0.1860 0.07820 0.07289 -0.1077 0.8346 0.0261
-9.750 -0.1960 0.07210 0.06678 -0.1121 0.8311 0.0256
-9.500 -0.2107 0.06690 0.06153 -0.1150 0.8273 0.0251
-9.250 -0.2275 0.06273 0.05728 -0.1161 0.8223 0.0247
-9.000 -0.2457 0.05914 0.05357 -0.1154 0.8178 0.0243
-8.750 -0.2650 0.05631 0.05058 -0.1130 0.8140 0.0240
-8.500 -0.2782 0.05351 0.04760 -0.1107 0.8091 0.0237
-8.250 -0.2868 0.05050 0.04433 -0.1084 0.8052 0.0234
-8.000 -0.2907 0.04751 0.04101 -0.1060 0.8021 0.0231
-7.750 -0.2905 0.04457 0.03769 -0.1037 0.7992 0.0230
-7.500 -0.2867 0.04210 0.03489 -0.1015 0.7947 0.0229
-7.250 -0.2784 0.03974 0.03216 -0.0996 0.7911 0.0229
-7.000 -0.2659 0.03755 0.02959 -0.0979 0.7883 0.0232
-6.750 -0.2498 0.03551 0.02715 -0.0965 0.7862 0.0236
-6.500 -0.2326 0.03401 0.02536 -0.0954 0.7833 0.0245
-6.250 -0.2148 0.03276 0.02382 -0.0942 0.7794 0.0260
-6.000 -0.1937 0.03149 0.02218 -0.0931 0.7764 0.0277
-5.750 -0.1702 0.02998 0.02041 -0.0924 0.7740 0.0286
-5.500 -0.1460 0.02854 0.01889 -0.0919 0.7721 0.0299
-5.250 -0.1219 0.02750 0.01774 -0.0914 0.7704 0.0316
-5.000 -0.1044 0.02698 0.01719 -0.0901 0.7660 0.0335
-4.750 -0.0838 0.02648 0.01656 -0.0890 0.7627 0.0372
-4.500 -0.0643 0.02567 0.01578 -0.0880 0.7600 0.0416
-4.250 -0.0429 0.02504 0.01505 -0.0869 0.7580 0.0471
-4.000 -0.0213 0.02441 0.01439 -0.0861 0.7563 0.0566
-3.750 -0.0084 0.02430 0.01429 -0.0841 0.7516 0.0677
-3.500 0.0085 0.02390 0.01401 -0.0827 0.7479 0.0937
-3.250 0.0248 0.02301 0.01371 -0.0812 0.7453 0.2016
-3.000 0.0309 0.02152 0.01354 -0.0780 0.7431 0.4826
-2.750 0.0471 0.02245 0.01539 -0.0714 0.7418 0.7163
-2.500 0.0488 0.02348 0.01636 -0.0670 0.7354 0.7630
-2.250 0.0605 0.02435 0.01707 -0.0634 0.7320 0.8040
-2.000 0.0776 0.02523 0.01785 -0.0592 0.7298 0.8361
-1.750 0.1004 0.02571 0.01818 -0.0564 0.7283 0.8626
-1.500 0.1326 0.02578 0.01805 -0.0563 0.7270 0.8773
-1.250 0.1242 0.02657 0.01885 -0.0508 0.7190 0.8897
-1.000 0.1537 0.02660 0.01872 -0.0512 0.7168 0.8965
-0.750 0.1761 0.02650 0.01849 -0.0504 0.7147 0.9036
-0.500 0.2107 0.02636 0.01818 -0.0518 0.7134 0.9074
-0.250 0.1950 0.02720 0.01905 -0.0455 0.7049 0.9172
0.000 0.2234 0.02722 0.01895 -0.0461 0.7024 0.9207
0.250 0.2509 0.02713 0.01875 -0.0463 0.7005 0.9243
0.500 0.2747 0.02698 0.01848 -0.0458 0.6989 0.9284
1.000 0.2917 0.02804 0.01949 -0.0415 0.6872 0.9381
1.250 0.3183 0.02792 0.01928 -0.0415 0.6855 0.9411
1.500 0.3470 0.02776 0.01905 -0.0419 0.6841 0.9435
2.000 0.3654 0.02905 0.02032 -0.0382 0.6716 0.9519
2.250 0.3964 0.02888 0.02011 -0.0390 0.6702 0.9538
2.750 0.4197 0.03026 0.02148 -0.0365 0.6577 0.9613
3.000 0.4533 0.03010 0.02129 -0.0377 0.6561 0.9627
3.250 0.4883 0.02987 0.02105 -0.0390 0.6550 0.9642
3.750 0.5162 0.03129 0.02252 -0.0374 0.6420 0.9712
4.000 0.5516 0.03108 0.02233 -0.0388 0.6406 0.9724
4.500 0.5911 0.03242 0.02376 -0.0393 0.6278 0.9789
4.750 0.6256 0.03211 0.02348 -0.0404 0.6264 0.9804
5.000 0.6308 0.03364 0.02507 -0.0396 0.6151 0.9859
5.250 0.6658 0.03326 0.02477 -0.0407 0.6133 0.9886
5.750 0.6918 0.03429 0.02588 -0.0383 0.5999 1.0000
6.000 0.7183 0.03394 0.02558 -0.0379 0.5974 1.0000
6.250 0.7160 0.03523 0.02695 -0.0352 0.5865 1.0000
6.500 0.7474 0.03475 0.02654 -0.0355 0.5846 1.0000
7.000 0.7804 0.03566 0.02759 -0.0340 0.5709 1.0000
7.500 0.8171 0.03647 0.02859 -0.0329 0.5572 1.0000
7.750 0.8514 0.03570 0.02793 -0.0335 0.5553 1.0000
8.250 0.8911 0.03628 0.02875 -0.0327 0.5409 1.0000
8.500 0.8991 0.03749 0.03006 -0.0316 0.5291 1.0000
9.000 0.9458 0.03746 0.03028 -0.0311 0.5141 1.0000
9.250 0.9591 0.03825 0.03122 -0.0303 0.5024 1.0000
9.750 1.0141 0.03735 0.03058 -0.0301 0.4845 1.0000
10.000 1.0328 0.03762 0.03097 -0.0295 0.4707 1.0000
10.250 1.0557 0.03752 0.03097 -0.0291 0.4557 1.0000
10.500 1.0740 0.03782 0.03137 -0.0284 0.4375 1.0000
10.750 1.0929 0.03804 0.03163 -0.0277 0.4159 1.0000
11.000 1.1107 0.03831 0.03187 -0.0268 0.3896 1.0000
11.250 1.1240 0.03901 0.03247 -0.0257 0.3594 1.0000
11.500 1.1319 0.04025 0.03357 -0.0245 0.3271 1.0000
12.000 1.1375 0.04399 0.03710 -0.0221 0.2640 1.0000
12.250 1.1368 0.04636 0.03934 -0.0210 0.2315 1.0000
12.500 1.1351 0.04894 0.04178 -0.0201 0.2005 1.0000
12.750 1.1312 0.05185 0.04452 -0.0192 0.1695 1.0000
13.000 1.1272 0.05491 0.04742 -0.0186 0.1409 1.0000
13.250 1.1244 0.05796 0.05035 -0.0181 0.1157 1.0000
13.500 1.1215 0.06114 0.05342 -0.0177 0.0938 1.0000
13.750 1.1188 0.06441 0.05660 -0.0175 0.0771 1.0000
14.000 1.1162 0.06775 0.05989 -0.0174 0.0641 1.0000
14.250 1.1155 0.07097 0.06312 -0.0175 0.0544 1.0000
14.500 1.1149 0.07426 0.06647 -0.0177 0.0467 1.0000
14.750 1.1117 0.07796 0.07015 -0.0180 0.0411 1.0000
15.000 1.1128 0.08119 0.07357 -0.0183 0.0362 1.0000
15.250 1.1090 0.08511 0.07750 -0.0190 0.0326 1.0000
15.500 1.1106 0.08837 0.08092 -0.0194 0.0296 1.0000
15.750 1.1109 0.09189 0.08455 -0.0201 0.0268 1.0000
16.000 1.1095 0.09564 0.08837 -0.0210 0.0249 1.0000
16.250 1.1107 0.09905 0.09190 -0.0217 0.0228 1.0000
16.500 1.1134 0.10228 0.09528 -0.0225 0.0211 1.0000
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Polar data table (+)
Polar graphs
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