YS-900 (ys900-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 100,000 Max Cl/Cd: 21.79 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys900-il-100000-n5.txt Download as CSV file: xf-ys900-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-900
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6292 0.09891 0.09430 -0.0331 1.0000 0.0402
-9.000 -0.6462 0.09624 0.09160 -0.0312 1.0000 0.0402
-8.750 -0.6644 0.09412 0.08946 -0.0280 1.0000 0.0402
-8.500 -0.6830 0.09205 0.08734 -0.0240 1.0000 0.0403
-8.250 -0.6981 0.08957 0.08477 -0.0204 1.0000 0.0404
-6.500 -0.7286 0.06367 0.05850 -0.0002 1.0000 0.0479
-5.000 -0.6924 0.04503 0.03804 0.0226 1.0000 0.0261
-4.750 -0.6846 0.04144 0.03413 0.0259 1.0000 0.0231
-4.500 -0.6719 0.03857 0.03088 0.0293 1.0000 0.0205
-4.250 -0.6543 0.03590 0.02764 0.0329 1.0000 0.0176
-4.000 -0.6327 0.03514 0.02648 0.0356 1.0000 0.0158
-3.750 -0.6145 0.03252 0.02353 0.0377 1.0000 0.0147
-3.500 -0.5947 0.03020 0.02084 0.0396 1.0000 0.0141
-3.250 -0.5718 0.02810 0.01839 0.0413 1.0000 0.0136
-3.000 -0.5465 0.02623 0.01622 0.0424 1.0000 0.0131
-2.750 -0.5204 0.02459 0.01435 0.0433 1.0000 0.0127
-2.500 -0.4956 0.02318 0.01278 0.0444 1.0000 0.0124
-2.250 -0.4743 0.02197 0.01144 0.0460 1.0000 0.0120
-2.000 -0.4562 0.02094 0.00989 0.0482 1.0000 0.0111
-1.750 -0.4382 0.02020 0.00896 0.0503 1.0000 0.0110
-1.500 -0.1819 0.02064 0.01223 0.0073 1.0000 0.9781
-1.250 -0.0799 0.02078 0.01199 -0.0091 1.0000 1.0000
-1.000 -0.0640 0.02069 0.01180 -0.0072 1.0000 1.0000
-0.750 -0.0481 0.02062 0.01166 -0.0054 1.0000 1.0000
-0.500 -0.0321 0.02057 0.01157 -0.0036 1.0000 1.0000
-0.250 -0.0160 0.02055 0.01151 -0.0018 1.0000 1.0000
0.000 0.0000 0.02054 0.01149 0.0000 1.0000 1.0000
0.250 0.0160 0.02055 0.01151 0.0018 1.0000 1.0000
0.500 0.0321 0.02057 0.01156 0.0036 1.0000 1.0000
0.750 0.0481 0.02062 0.01166 0.0054 1.0000 1.0000
1.000 0.0640 0.02069 0.01180 0.0072 1.0000 1.0000
1.250 0.0799 0.02077 0.01197 0.0091 1.0000 1.0000
1.500 0.0957 0.02088 0.01218 0.0109 1.0000 1.0000
1.750 0.4382 0.02022 0.00898 -0.0503 0.0110 1.0000
2.000 0.4562 0.02094 0.00990 -0.0482 0.0111 1.0000
2.250 0.4743 0.02199 0.01145 -0.0460 0.0120 1.0000
2.500 0.4957 0.02319 0.01279 -0.0444 0.0123 1.0000
2.750 0.5205 0.02461 0.01438 -0.0434 0.0128 1.0000
3.000 0.5468 0.02627 0.01627 -0.0425 0.0132 1.0000
3.250 0.5717 0.02805 0.01835 -0.0413 0.0136 1.0000
3.500 0.5947 0.03018 0.02082 -0.0397 0.0141 1.0000
3.750 0.6146 0.03259 0.02360 -0.0377 0.0148 1.0000
4.000 0.6323 0.03530 0.02665 -0.0356 0.0157 1.0000
4.250 0.6544 0.03591 0.02765 -0.0329 0.0176 1.0000
4.500 0.6719 0.03856 0.03086 -0.0293 0.0205 1.0000
4.750 0.6846 0.04151 0.03419 -0.0258 0.0233 1.0000
5.000 0.6921 0.04518 0.03817 -0.0227 0.0263 1.0000
5.250 0.7231 0.04930 0.04297 -0.0182 0.0692 1.0000
5.500 0.7248 0.05191 0.04590 -0.0143 0.0605 1.0000
5.750 0.7300 0.05460 0.04879 -0.0109 0.0574 1.0000
6.000 0.7345 0.05795 0.05220 -0.0081 0.0552 1.0000
6.250 0.7395 0.06551 0.05949 -0.0073 0.0533 1.0000
6.500 0.7287 0.06366 0.05850 0.0002 0.0480 1.0000
6.750 0.7262 0.06661 0.06161 0.0037 0.0460 1.0000
7.000 0.7227 0.06961 0.06473 0.0071 0.0445 1.0000
7.250 0.7182 0.07269 0.06789 0.0104 0.0433 1.0000
7.500 0.7142 0.07600 0.07124 0.0133 0.0422 1.0000
7.750 0.7121 0.08011 0.07532 0.0157 0.0414 1.0000
8.000 0.7095 0.08706 0.08215 0.0168 0.0404 1.0000
8.250 0.6978 0.08957 0.08477 0.0204 0.0404 1.0000
8.500 0.6825 0.09193 0.08723 0.0240 0.0403 1.0000
8.750 0.6653 0.09417 0.08951 0.0278 0.0402 1.0000
9.000 0.6460 0.09628 0.09164 0.0312 0.0402 1.0000
9.250 0.6289 0.09889 0.09428 0.0331 0.0402 1.0000
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Polar data table (+)
Polar graphs
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