YS-930 (ys930-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.38 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys930-il-1000000.txt Download as CSV file: xf-ys930-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: YS-930
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4340 0.13383 0.13215 -0.0364 1.0000 0.0063
-12.250 -0.4327 0.13010 0.12843 -0.0371 1.0000 0.0063
-9.250 -0.4439 0.04089 0.03891 -0.1127 0.9571 0.0068
-9.000 -0.4326 0.03417 0.03179 -0.1221 0.9418 0.0071
-8.750 -0.4238 0.03047 0.02773 -0.1238 0.9244 0.0073
-8.500 -0.4064 0.02982 0.02700 -0.1240 0.9145 0.0079
-8.250 -0.3974 0.02747 0.02434 -0.1230 0.9048 0.0081
-7.750 -0.3790 0.02080 0.01677 -0.1190 0.8910 0.0069
-7.500 -0.3608 0.01913 0.01487 -0.1179 0.8866 0.0068
-7.250 -0.3384 0.01827 0.01386 -0.1173 0.8830 0.0067
-7.000 -0.3225 0.01543 0.01073 -0.1157 0.8793 0.0059
-6.750 -0.3033 0.01364 0.00871 -0.1144 0.8763 0.0057
-6.500 -0.2825 0.01236 0.00726 -0.1133 0.8734 0.0056
-6.250 -0.2606 0.01133 0.00607 -0.1124 0.8707 0.0056
-6.000 -0.2372 0.01053 0.00511 -0.1116 0.8683 0.0059
-5.750 -0.2119 0.01002 0.00447 -0.1113 0.8661 0.0063
-5.500 -0.1880 0.00917 0.00342 -0.1106 0.8639 0.0099
-5.250 -0.1620 0.00880 0.00298 -0.1103 0.8622 0.0152
-5.000 -0.1355 0.00850 0.00267 -0.1102 0.8604 0.0231
-4.750 -0.1112 0.00787 0.00228 -0.1099 0.8586 0.0767
-4.500 -0.0870 0.00728 0.00204 -0.1096 0.8569 0.1670
-4.250 -0.0594 0.00718 0.00195 -0.1097 0.8554 0.1841
-4.000 -0.0317 0.00711 0.00186 -0.1098 0.8540 0.1966
-3.750 -0.0037 0.00706 0.00178 -0.1100 0.8526 0.2041
-3.500 0.0243 0.00703 0.00174 -0.1102 0.8511 0.2140
-3.250 0.0517 0.00696 0.00170 -0.1102 0.8498 0.2262
-3.000 0.0793 0.00689 0.00163 -0.1103 0.8486 0.2332
-2.750 0.1070 0.00683 0.00157 -0.1104 0.8473 0.2400
-2.500 0.1347 0.00677 0.00152 -0.1105 0.8460 0.2468
-2.250 0.1625 0.00671 0.00147 -0.1106 0.8446 0.2541
-2.000 0.1902 0.00664 0.00143 -0.1107 0.8432 0.2631
-1.750 0.2181 0.00658 0.00139 -0.1108 0.8419 0.2749
-1.500 0.2458 0.00652 0.00137 -0.1110 0.8406 0.2899
-1.250 0.2737 0.00647 0.00137 -0.1111 0.8392 0.3083
-1.000 0.3015 0.00643 0.00140 -0.1113 0.8378 0.3310
-0.750 0.3285 0.00633 0.00141 -0.1112 0.8364 0.3585
-0.500 0.3554 0.00623 0.00143 -0.1112 0.8346 0.3919
-0.250 0.3823 0.00612 0.00145 -0.1111 0.8326 0.4313
0.000 0.4092 0.00599 0.00147 -0.1111 0.8303 0.4775
0.250 0.4361 0.00584 0.00148 -0.1110 0.8275 0.5313
0.500 0.4628 0.00572 0.00154 -0.1108 0.8243 0.5971
0.750 0.4872 0.00549 0.00157 -0.1102 0.8207 0.6721
1.000 0.5115 0.00525 0.00160 -0.1094 0.8165 0.7564
1.250 0.5350 0.00502 0.00164 -0.1083 0.8123 0.8482
1.500 0.5668 0.00484 0.00173 -0.1089 0.8072 0.9435
1.750 0.6095 0.00480 0.00172 -0.1122 0.8005 0.9757
2.000 0.6451 0.00478 0.00171 -0.1139 0.7914 0.9881
2.250 0.6812 0.00473 0.00163 -0.1156 0.7736 0.9955
2.500 0.7185 0.00472 0.00164 -0.1178 0.7556 1.0000
2.750 0.7396 0.00476 0.00167 -0.1163 0.7332 1.0000
3.000 0.7364 0.00550 0.00181 -0.1094 0.5962 1.0000
3.250 0.7287 0.00672 0.00229 -0.1021 0.4336 1.0000
3.500 0.7266 0.00790 0.00275 -0.0962 0.2759 1.0000
3.750 0.7316 0.00894 0.00320 -0.0919 0.1452 1.0000
4.000 0.7446 0.00967 0.00358 -0.0891 0.0671 1.0000
4.250 0.7612 0.01025 0.00394 -0.0870 0.0223 1.0000
4.500 0.7762 0.01105 0.00476 -0.0842 0.0070 1.0000
4.750 0.7966 0.01146 0.00526 -0.0827 0.0068 1.0000
5.000 0.8155 0.01200 0.00587 -0.0808 0.0066 1.0000
5.250 0.8329 0.01268 0.00664 -0.0787 0.0064 1.0000
5.500 0.8510 0.01331 0.00734 -0.0768 0.0061 1.0000
5.750 0.8706 0.01378 0.00783 -0.0752 0.0055 1.0000
6.000 0.8881 0.01452 0.00864 -0.0733 0.0054 1.0000
6.250 0.9067 0.01535 0.00954 -0.0715 0.0051 1.0000
6.500 0.9270 0.01603 0.01026 -0.0702 0.0048 1.0000
6.750 0.9487 0.01702 0.01136 -0.0692 0.0046 1.0000
7.000 0.9708 0.01817 0.01255 -0.0684 0.0040 1.0000
7.250 1.0045 0.02441 0.01933 -0.0693 0.0036 1.0000
7.500 1.0247 0.02564 0.02070 -0.0679 0.0037 1.0000
7.750 1.0441 0.02678 0.02198 -0.0663 0.0038 1.0000
16.750 0.8792 0.21102 0.20941 -0.0874 0.0036 1.0000
17.000 0.8857 0.21509 0.21347 -0.0894 0.0036 1.0000
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Polar data table (+)
Polar graphs
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