YS-930 (ys930-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 200,000 Max Cl/Cd: 75.55 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys930-il-200000-n5.txt Download as CSV file: xf-ys930-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4354 0.10781 0.10432 -0.0435 1.0000 0.0078
-10.500 -0.4419 0.10330 0.09990 -0.0441 1.0000 0.0085
-10.250 -0.4452 0.09989 0.09655 -0.0442 0.9997 0.0084
-10.000 -0.4416 0.09456 0.09121 -0.0482 0.9971 0.0077
-9.750 -0.4351 0.08839 0.08505 -0.0531 0.9940 0.0081
-9.500 -0.4325 0.08171 0.07839 -0.0580 0.9896 0.0082
-9.250 -0.4354 0.07370 0.07040 -0.0646 0.9844 0.0080
-9.000 -0.4448 0.06499 0.06170 -0.0723 0.9756 0.0075
-8.750 -0.4563 0.05380 0.05042 -0.0856 0.9631 0.0070
-8.500 -0.4587 0.04525 0.04150 -0.0976 0.9516 0.0069
-8.250 -0.4539 0.03895 0.03470 -0.1030 0.9455 0.0065
-8.000 -0.4416 0.03569 0.03101 -0.1044 0.9393 0.0073
-7.750 -0.4217 0.03343 0.02832 -0.1054 0.9353 0.0081
-7.500 -0.4026 0.03011 0.02450 -0.1065 0.9324 0.0082
-7.250 -0.3852 0.02754 0.02150 -0.1062 0.9283 0.0083
-7.000 -0.3673 0.02486 0.01842 -0.1056 0.9242 0.0084
-6.750 -0.3466 0.02194 0.01512 -0.1053 0.9214 0.0088
-6.500 -0.3227 0.01988 0.01281 -0.1054 0.9194 0.0094
-6.250 -0.2986 0.01851 0.01120 -0.1052 0.9172 0.0103
-6.000 -0.2792 0.01756 0.01012 -0.1040 0.9132 0.0121
-5.750 -0.2548 0.01675 0.00913 -0.1036 0.9105 0.0150
-5.500 -0.2291 0.01580 0.00803 -0.1036 0.9082 0.0209
-5.250 -0.2011 0.01511 0.00716 -0.1040 0.9065 0.0294
-5.000 -0.1732 0.01429 0.00627 -0.1043 0.9051 0.0485
-4.750 -0.1544 0.01339 0.00578 -0.1032 0.9019 0.1335
-4.500 -0.1299 0.01323 0.00571 -0.1028 0.8993 0.1910
-4.250 -0.1032 0.01318 0.00562 -0.1028 0.8973 0.2202
-4.000 -0.0756 0.01312 0.00548 -0.1030 0.8955 0.2426
-3.750 -0.0468 0.01300 0.00526 -0.1034 0.8940 0.2530
-3.500 -0.0173 0.01286 0.00503 -0.1039 0.8927 0.2612
-3.250 0.0122 0.01270 0.00483 -0.1044 0.8915 0.2679
-3.000 0.0326 0.01272 0.00481 -0.1031 0.8884 0.2750
-2.750 0.0567 0.01265 0.00471 -0.1025 0.8859 0.2820
-2.500 0.0832 0.01259 0.00461 -0.1024 0.8838 0.2906
-2.250 0.1103 0.01250 0.00453 -0.1025 0.8821 0.3006
-2.000 0.1384 0.01241 0.00446 -0.1027 0.8807 0.3138
-1.750 0.1672 0.01231 0.00439 -0.1031 0.8794 0.3299
-1.500 0.1956 0.01222 0.00433 -0.1034 0.8781 0.3483
-1.250 0.2140 0.01229 0.00449 -0.1017 0.8744 0.3688
-1.000 0.2377 0.01227 0.00457 -0.1011 0.8718 0.3954
-0.750 0.2635 0.01219 0.00463 -0.1009 0.8698 0.4296
-0.500 0.2905 0.01207 0.00468 -0.1009 0.8681 0.4736
-0.250 0.3179 0.01191 0.00474 -0.1009 0.8666 0.5302
0.000 0.3455 0.01170 0.00480 -0.1010 0.8652 0.6021
0.250 0.3601 0.01170 0.00510 -0.0983 0.8608 0.6766
0.500 0.3819 0.01153 0.00529 -0.0969 0.8579 0.7776
0.750 0.4361 0.01133 0.00545 -0.1022 0.8578 0.9210
1.000 0.4895 0.01132 0.00551 -0.1080 0.8572 0.9976
1.250 0.5184 0.01137 0.00558 -0.1083 0.8548 1.0000
1.500 0.5483 0.01138 0.00562 -0.1087 0.8526 1.0000
1.750 0.5658 0.01158 0.00590 -0.1067 0.8473 1.0000
2.000 0.5906 0.01163 0.00599 -0.1060 0.8427 1.0000
2.250 0.6231 0.01153 0.00596 -0.1068 0.8394 1.0000
2.500 0.6418 0.01164 0.00614 -0.1048 0.8321 1.0000
2.750 0.6761 0.01139 0.00597 -0.1057 0.8259 1.0000
3.000 0.6991 0.01123 0.00590 -0.1042 0.8144 1.0000
3.250 0.7233 0.01082 0.00560 -0.1026 0.7943 1.0000
3.500 0.7403 0.01037 0.00514 -0.0992 0.7539 1.0000
3.750 0.7600 0.01006 0.00442 -0.0962 0.6299 1.0000
4.000 0.7574 0.01121 0.00464 -0.0896 0.4685 1.0000
4.250 0.7489 0.01272 0.00532 -0.0828 0.3105 1.0000
4.500 0.7457 0.01436 0.00609 -0.0774 0.1477 1.0000
4.750 0.7515 0.01574 0.00687 -0.0738 0.0460 1.0000
5.000 0.7650 0.01665 0.00764 -0.0711 0.0207 1.0000
5.250 0.7805 0.01746 0.00853 -0.0687 0.0138 1.0000
5.500 0.7964 0.01827 0.00944 -0.0665 0.0115 1.0000
5.750 0.8111 0.01925 0.01052 -0.0641 0.0102 1.0000
6.000 0.8242 0.02074 0.01218 -0.0614 0.0093 1.0000
6.250 0.8446 0.02248 0.01402 -0.0601 0.0086 1.0000
6.500 0.8663 0.02306 0.01470 -0.0591 0.0069 1.0000
6.750 0.8880 0.02393 0.01566 -0.0582 0.0056 1.0000
7.000 0.9141 0.02551 0.01740 -0.0580 0.0052 1.0000
7.250 0.9407 0.02748 0.01954 -0.0580 0.0047 1.0000
7.500 0.9667 0.02983 0.02217 -0.0577 0.0046 1.0000
7.750 0.9881 0.03352 0.02630 -0.0566 0.0043 1.0000
8.000 1.0013 0.03732 0.03058 -0.0542 0.0042 1.0000
8.250 1.0107 0.04020 0.03383 -0.0514 0.0043 1.0000
8.500 1.0150 0.04341 0.03742 -0.0480 0.0043 1.0000
8.750 1.0170 0.04630 0.04063 -0.0445 0.0043 1.0000
9.000 1.0137 0.04925 0.04388 -0.0404 0.0043 1.0000
9.250 1.0088 0.05188 0.04676 -0.0362 0.0043 1.0000
9.500 0.9997 0.05486 0.04999 -0.0320 0.0044 1.0000
9.750 0.9921 0.05772 0.05316 -0.0284 0.0045 1.0000
10.000 0.9789 0.06125 0.05692 -0.0250 0.0045 1.0000
10.250 0.9656 0.06539 0.06129 -0.0222 0.0047 1.0000
10.500 0.9468 0.06983 0.06585 -0.0202 0.0047 1.0000
10.750 0.9273 0.07502 0.07124 -0.0192 0.0049 1.0000
11.000 0.9039 0.08149 0.07790 -0.0197 0.0051 1.0000
11.250 0.8809 0.08863 0.08518 -0.0222 0.0052 1.0000
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Polar data table (+)
Polar graphs
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