YS-900 (ys900-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 500,000 Max Cl/Cd: 33.4 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys900-il-500000-n5.txt Download as CSV file: xf-ys900-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5504 0.05902 0.05622 -0.0522 0.9725 0.0062
-7.500 -0.5602 0.05431 0.05134 -0.0489 0.9709 0.0065
-7.250 -0.5657 0.05016 0.04702 -0.0457 0.9697 0.0067
-7.000 -0.5637 0.04690 0.04356 -0.0428 0.9689 0.0069
-6.750 -0.5787 0.04528 0.04184 -0.0352 0.9656 0.0071
-6.500 -0.5823 0.04315 0.03957 -0.0302 0.9634 0.0074
-6.250 -0.5785 0.04078 0.03704 -0.0267 0.9614 0.0077
-6.000 -0.5715 0.03845 0.03452 -0.0234 0.9600 0.0081
-5.750 -0.5614 0.03621 0.03204 -0.0206 0.9588 0.0087
-5.500 -0.5471 0.03381 0.02940 -0.0182 0.9577 0.0095
-5.250 -0.5307 0.03147 0.02680 -0.0159 0.9568 0.0103
-5.000 -0.5122 0.02937 0.02443 -0.0138 0.9561 0.0114
-4.750 -0.5138 0.02817 0.02306 -0.0071 0.9521 0.0123
-4.500 -0.4944 0.02760 0.02230 -0.0046 0.9502 0.0145
-4.250 -0.4733 0.02754 0.02199 -0.0024 0.9485 0.0154
-3.000 -0.3402 0.01621 0.00939 0.0008 0.9460 0.0113
-2.750 -0.3117 0.01496 0.00800 0.0013 0.9456 0.0074
-2.500 -0.2832 0.01481 0.00783 0.0011 0.9449 0.0061
-2.250 -0.2610 0.01370 0.00663 0.0024 0.9441 0.0055
-2.000 -0.2354 0.01308 0.00590 0.0029 0.9434 0.0049
-1.750 -0.2334 0.01288 0.00562 0.0086 0.9380 0.0046
-1.500 -0.2102 0.01262 0.00524 0.0096 0.9360 0.0043
-1.250 -0.1834 0.01244 0.00498 0.0097 0.9345 0.0042
-1.000 -0.1547 0.01232 0.00482 0.0093 0.9334 0.0042
-0.750 -0.1248 0.01219 0.00464 0.0086 0.9324 0.0059
-0.500 -0.0717 0.01175 0.00762 0.0042 0.9362 0.9324
-0.250 -0.0352 0.01182 0.00767 0.0020 0.9354 0.9335
0.000 -0.0001 0.01184 0.00768 0.0000 0.9345 0.9345
0.250 0.0350 0.01182 0.00767 -0.0019 0.9335 0.9354
0.500 0.0717 0.01175 0.00762 -0.0042 0.9324 0.9362
0.750 0.1249 0.01219 0.00465 -0.0086 0.0060 0.9324
1.000 0.1547 0.01232 0.00481 -0.0093 0.0042 0.9334
1.250 0.1835 0.01244 0.00497 -0.0097 0.0041 0.9345
1.500 0.2102 0.01261 0.00523 -0.0096 0.0043 0.9360
1.750 0.2333 0.01288 0.00563 -0.0086 0.0047 0.9380
2.000 0.2355 0.01307 0.00589 -0.0029 0.0049 0.9434
2.250 0.2612 0.01369 0.00661 -0.0024 0.0054 0.9441
2.500 0.2834 0.01480 0.00783 -0.0012 0.0062 0.9449
2.750 0.3117 0.01499 0.00804 -0.0013 0.0073 0.9456
3.000 0.3406 0.01626 0.00944 -0.0008 0.0116 0.9459
4.750 0.4873 0.01459 0.00975 0.0100 0.0126 0.9508
5.000 0.4920 0.01583 0.01120 0.0150 0.0117 0.9544
5.250 0.5002 0.01745 0.01304 0.0191 0.0108 0.9566
5.500 0.5156 0.01985 0.01570 0.0213 0.0099 0.9575
5.750 0.5278 0.02230 0.01838 0.0239 0.0092 0.9585
6.000 0.5379 0.02490 0.02124 0.0266 0.0085 0.9599
6.250 0.5442 0.02754 0.02406 0.0297 0.0080 0.9615
6.500 0.5460 0.02998 0.02667 0.0335 0.0077 0.9634
6.750 0.5417 0.03221 0.02903 0.0384 0.0074 0.9661
7.000 0.5302 0.03386 0.03078 0.0449 0.0073 0.9690
7.250 0.5311 0.03736 0.03444 0.0475 0.0070 0.9699
7.500 0.5270 0.04101 0.03824 0.0506 0.0068 0.9710
7.750 0.5189 0.04474 0.04210 0.0540 0.0066 0.9724
8.000 0.5104 0.04831 0.04579 0.0572 0.0066 0.9743
8.250 0.4912 0.05102 0.04858 0.0623 0.0065 0.9766
8.500 0.4755 0.05322 0.05085 0.0666 0.0065 0.9788
8.750 0.4567 0.05531 0.05300 0.0709 0.0065 0.9811
9.000 0.4437 0.05906 0.05682 0.0716 0.0065 0.9819
9.250 0.4346 0.06344 0.06128 0.0701 0.0066 0.9825
9.500 0.4253 0.06902 0.06692 0.0662 0.0067 0.9831
9.750 0.4192 0.07528 0.07318 0.0611 0.0068 0.9835
10.000 0.4147 0.08054 0.07843 0.0585 0.0069 0.9839
10.250 0.4103 0.08553 0.08340 0.0565 0.0068 0.9843
10.500 0.4066 0.09031 0.08817 0.0548 0.0067 0.9847
10.750 0.4027 0.09507 0.09292 0.0533 0.0066 0.9850
11.000 0.3937 0.10095 0.09878 0.0518 0.0063 0.9853
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Polar data table (+)
Polar graphs
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