AH 95-160 (ah95160-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 200,000 Max Cl/Cd: 73.66 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah95160-il-200000-n5.txt Download as CSV file: xf-ah95160-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 95-160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1990 0.09273 0.08775 -0.0730 0.7161 0.0243
-10.000 -0.3811 0.04498 0.03967 -0.1114 0.7165 0.0232
-9.750 -0.4033 0.03708 0.03104 -0.1156 0.7143 0.0234
-9.500 -0.3880 0.03525 0.02907 -0.1163 0.7121 0.0237
-9.250 -0.3704 0.03362 0.02727 -0.1168 0.7099 0.0241
-9.000 -0.3513 0.03213 0.02557 -0.1172 0.7076 0.0247
-8.750 -0.3323 0.03032 0.02348 -0.1176 0.7054 0.0255
-8.500 -0.3132 0.02814 0.02086 -0.1178 0.7034 0.0265
-8.250 -0.2922 0.02617 0.01842 -0.1180 0.7017 0.0274
-7.750 -0.2426 0.02447 0.01654 -0.1184 0.6981 0.0287
-7.500 -0.2173 0.02356 0.01548 -0.1187 0.6961 0.0296
-7.250 -0.1917 0.02258 0.01430 -0.1188 0.6940 0.0307
-7.000 -0.1657 0.02175 0.01330 -0.1190 0.6919 0.0320
-6.750 -0.1389 0.02129 0.01282 -0.1192 0.6898 0.0333
-6.500 -0.1120 0.02073 0.01213 -0.1194 0.6878 0.0351
-6.250 -0.0851 0.02006 0.01130 -0.1195 0.6862 0.0368
-6.000 -0.0580 0.01962 0.01083 -0.1197 0.6847 0.0384
-5.750 -0.0304 0.01920 0.01030 -0.1199 0.6833 0.0408
-5.500 -0.0030 0.01880 0.00987 -0.1202 0.6814 0.0434
-5.250 0.0246 0.01849 0.00956 -0.1205 0.6792 0.0463
-5.000 0.0521 0.01811 0.00913 -0.1207 0.6770 0.0495
-4.750 0.0800 0.01787 0.00888 -0.1210 0.6749 0.0534
-4.500 0.1079 0.01758 0.00856 -0.1212 0.6731 0.0575
-4.250 0.1361 0.01736 0.00830 -0.1215 0.6714 0.0624
-4.000 0.1642 0.01711 0.00803 -0.1218 0.6698 0.0674
-3.750 0.1927 0.01693 0.00779 -0.1221 0.6683 0.0734
-3.500 0.2211 0.01670 0.00754 -0.1224 0.6668 0.0795
-3.250 0.2494 0.01656 0.00737 -0.1227 0.6650 0.0863
-3.000 0.2771 0.01638 0.00726 -0.1230 0.6629 0.0939
-2.750 0.3052 0.01625 0.00714 -0.1234 0.6609 0.1021
-2.500 0.3335 0.01614 0.00704 -0.1237 0.6589 0.1125
-2.250 0.3618 0.01598 0.00694 -0.1241 0.6570 0.1261
-2.000 0.3903 0.01582 0.00683 -0.1245 0.6551 0.1466
-1.750 0.4189 0.01558 0.00673 -0.1250 0.6534 0.1863
-1.500 0.4474 0.01523 0.00665 -0.1256 0.6518 0.2693
-1.250 0.4756 0.01476 0.00663 -0.1262 0.6505 0.4090
-1.000 0.5027 0.01440 0.00674 -0.1263 0.6492 0.5537
-0.750 0.5280 0.01436 0.00700 -0.1260 0.6469 0.6411
-0.500 0.5535 0.01440 0.00720 -0.1255 0.6445 0.6963
-0.250 0.5787 0.01444 0.00735 -0.1249 0.6422 0.7399
0.000 0.6038 0.01450 0.00748 -0.1243 0.6401 0.7766
0.250 0.6270 0.01455 0.00760 -0.1230 0.6384 0.8201
0.500 0.6459 0.01456 0.00770 -0.1207 0.6367 0.8709
0.750 0.6651 0.01454 0.00771 -0.1184 0.6352 0.9133
1.000 0.6912 0.01452 0.00765 -0.1177 0.6338 0.9415
1.250 0.7227 0.01461 0.00773 -0.1187 0.6318 0.9641
1.500 0.7574 0.01481 0.00794 -0.1206 0.6292 0.9906
1.750 0.7858 0.01502 0.00815 -0.1213 0.6268 0.9998
2.000 0.8138 0.01521 0.00831 -0.1218 0.6245 0.9998
2.250 0.8424 0.01536 0.00841 -0.1223 0.6224 0.9998
2.500 0.8716 0.01548 0.00850 -0.1229 0.6206 0.9998
2.750 0.9011 0.01561 0.00857 -0.1235 0.6190 0.9998
3.000 0.9309 0.01572 0.00864 -0.1241 0.6177 0.9998
3.250 0.9571 0.01602 0.00896 -0.1243 0.6151 0.9998
3.500 0.9818 0.01638 0.00938 -0.1243 0.6118 0.9998
3.750 1.0081 0.01664 0.00967 -0.1244 0.6091 0.9998
4.000 1.0356 0.01682 0.00986 -0.1247 0.6068 0.9998
4.250 1.0639 0.01695 0.00999 -0.1251 0.6048 0.9998
4.500 1.0932 0.01704 0.01007 -0.1256 0.6031 0.9998
4.750 1.1231 0.01711 0.01012 -0.1261 0.6015 0.9998
5.000 1.1437 0.01763 0.01076 -0.1255 0.5974 0.9998
5.250 1.1673 0.01798 0.01117 -0.1253 0.5939 0.9998
5.500 1.1937 0.01813 0.01137 -0.1253 0.5909 0.9998
5.750 1.2223 0.01816 0.01140 -0.1257 0.5884 0.9998
6.000 1.2529 0.01808 0.01132 -0.1262 0.5862 0.9998
6.250 1.2702 0.01861 0.01199 -0.1251 0.5806 0.9998
6.500 1.2939 0.01874 0.01218 -0.1247 0.5758 0.9998
6.750 1.3239 0.01852 0.01194 -0.1250 0.5719 0.9998
7.000 1.3419 0.01885 0.01238 -0.1238 0.5651 0.9998
7.250 1.3653 0.01882 0.01239 -0.1232 0.5584 0.9998
7.500 1.3857 0.01895 0.01258 -0.1222 0.5509 0.9998
7.750 1.4055 0.01908 0.01275 -0.1212 0.5427 0.9998
8.000 1.4201 0.01946 0.01320 -0.1194 0.5344 0.9998
8.250 1.4384 0.01964 0.01341 -0.1181 0.5265 0.9998
8.500 1.4470 0.02039 0.01425 -0.1157 0.5171 0.9998
8.750 1.4630 0.02080 0.01469 -0.1144 0.5077 0.9998
9.000 1.4735 0.02159 0.01552 -0.1125 0.4965 0.9998
9.250 1.4813 0.02266 0.01663 -0.1106 0.4839 0.9998
9.500 1.4903 0.02371 0.01771 -0.1089 0.4693 0.9998
9.750 1.4984 0.02486 0.01884 -0.1072 0.4522 0.9998
10.000 1.5044 0.02619 0.02010 -0.1053 0.4321 0.9998
10.250 1.5058 0.02792 0.02175 -0.1032 0.4079 0.9998
10.500 1.5031 0.02999 0.02368 -0.1007 0.3816 0.9998
10.750 1.4958 0.03247 0.02601 -0.0981 0.3548 0.9998
11.000 1.4868 0.03519 0.02859 -0.0955 0.3287 0.9998
11.250 1.4776 0.03798 0.03127 -0.0930 0.3045 0.9998
11.500 1.4691 0.04087 0.03404 -0.0907 0.2817 0.9998
11.750 1.4619 0.04376 0.03682 -0.0888 0.2607 0.9998
12.000 1.4569 0.04656 0.03955 -0.0870 0.2405 0.9998
12.250 1.4524 0.04940 0.04231 -0.0855 0.2220 0.9998
12.500 1.4490 0.05221 0.04505 -0.0841 0.2051 0.9998
12.750 1.4470 0.05495 0.04774 -0.0828 0.1895 0.9998
13.000 1.4458 0.05766 0.05041 -0.0817 0.1753 0.9998
13.250 1.4460 0.06028 0.05299 -0.0807 0.1623 0.9998
13.500 1.4465 0.06290 0.05560 -0.0797 0.1507 0.9998
13.750 1.4474 0.06551 0.05819 -0.0789 0.1402 0.9998
14.250 1.4507 0.07069 0.06338 -0.0774 0.1220 0.9998
14.500 1.4522 0.07332 0.06603 -0.0768 0.1145 0.9998
14.750 1.4541 0.07596 0.06867 -0.0762 0.1072 0.9998
15.000 1.4569 0.07852 0.07127 -0.0757 0.1010 0.9998
15.250 1.4585 0.08124 0.07401 -0.0753 0.0952 0.9998
15.500 1.4612 0.08384 0.07667 -0.0749 0.0900 0.9998
15.750 1.4633 0.08654 0.07941 -0.0746 0.0849 0.9998
16.000 1.4644 0.08938 0.08228 -0.0743 0.0807 0.9998
16.250 1.4677 0.09198 0.08496 -0.0741 0.0764 0.9998
16.500 1.4681 0.09497 0.08798 -0.0740 0.0725 0.9998
16.750 1.4706 0.09772 0.09081 -0.0739 0.0690 0.9998
17.000 1.4725 0.10054 0.09371 -0.0739 0.0656 0.9998
17.250 1.4719 0.10372 0.09691 -0.0740 0.0627 0.9998
17.500 1.4743 0.10653 0.09981 -0.0741 0.0598 0.9998
17.750 1.4760 0.10943 0.10280 -0.0743 0.0570 0.9998
18.000 1.4753 0.11272 0.10613 -0.0747 0.0546 0.9998
18.250 1.4762 0.11578 0.10926 -0.0751 0.0525 0.9998
18.500 1.4781 0.11873 0.11232 -0.0756 0.0502 0.9998
18.750 1.4784 0.12193 0.11559 -0.0762 0.0481 0.9998
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Polar data table (+)
Polar graphs
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