GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 411 AIRFOIL (goe411-il) Reynolds number: 200,000 Max Cl/Cd: 35.59 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe411-il-200000-n5.txt Download as CSV file: xf-goe411-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 411 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6375 0.09774 0.09384 -0.0370 1.0000 0.0086
-13.000 -0.6531 0.09115 0.08706 -0.0427 1.0000 0.0091
-12.750 -0.6727 0.08378 0.07970 -0.0449 1.0000 0.0082
-12.500 -0.6896 0.07794 0.07372 -0.0485 1.0000 0.0084
-12.250 -0.7086 0.07220 0.06786 -0.0511 1.0000 0.0082
-12.000 -0.7205 0.06936 0.06480 -0.0530 1.0000 0.0089
-11.750 -0.7456 0.06254 0.05791 -0.0538 1.0000 0.0076
-11.500 -0.7576 0.05975 0.05494 -0.0536 1.0000 0.0082
-11.250 -0.7753 0.05601 0.05103 -0.0525 1.0000 0.0079
-11.000 -0.7854 0.05462 0.04944 -0.0504 1.0000 0.0086
-10.750 -0.7993 0.05186 0.04652 -0.0476 1.0000 0.0085
-10.500 -0.8138 0.04900 0.04349 -0.0441 1.0000 0.0082
-10.250 -0.8259 0.05010 0.04439 -0.0384 1.0000 0.0090
-9.750 -0.8475 0.04569 0.03965 -0.0287 1.0000 0.0089
-9.500 -0.8547 0.04485 0.03860 -0.0236 1.0000 0.0091
-9.250 -0.8569 0.04238 0.03592 -0.0196 1.0000 0.0090
-9.000 -0.8565 0.04001 0.03333 -0.0158 1.0000 0.0089
-8.750 -0.8537 0.03806 0.03117 -0.0121 1.0000 0.0089
-8.500 -0.8487 0.03614 0.02902 -0.0086 1.0000 0.0089
-8.250 -0.8412 0.03438 0.02705 -0.0054 1.0000 0.0090
-8.000 -0.8313 0.03271 0.02519 -0.0025 1.0000 0.0090
-7.750 -0.8205 0.03137 0.02367 0.0004 1.0000 0.0091
-7.500 -0.8074 0.02991 0.02201 0.0029 1.0000 0.0092
-7.250 -0.7895 0.02766 0.01964 0.0044 1.0000 0.0094
-7.000 -0.7742 0.02564 0.01758 0.0064 1.0000 0.0097
-6.750 -0.7638 0.02432 0.01623 0.0093 1.0000 0.0100
-6.500 -0.7485 0.02316 0.01508 0.0109 0.9988 0.0113
-6.250 -0.7178 0.02197 0.01383 0.0095 0.9947 0.0125
-6.000 -0.6893 0.02078 0.01258 0.0087 0.9896 0.0130
-5.750 -0.6606 0.01968 0.01137 0.0079 0.9844 0.0139
-5.500 -0.6314 0.01879 0.01034 0.0071 0.9791 0.0149
-5.250 -0.6027 0.01819 0.00958 0.0066 0.9739 0.0163
-5.000 -0.5746 0.01731 0.00849 0.0062 0.9694 0.0186
-4.750 -0.5481 0.01673 0.00775 0.0062 0.9638 0.0212
-4.500 -0.5174 0.01620 0.00710 0.0055 0.9595 0.0274
-4.250 -0.5015 0.01479 0.00628 0.0070 0.9522 0.1512
-4.000 -0.4790 0.01355 0.00573 0.0072 0.9475 0.2735
-3.750 -0.4598 0.01289 0.00541 0.0085 0.9395 0.3497
-3.500 -0.4346 0.01227 0.00518 0.0087 0.9346 0.4397
-3.250 -0.4146 0.01189 0.00502 0.0103 0.9264 0.5015
-3.000 -0.3806 0.01163 0.00476 0.0089 0.9228 0.5233
-2.750 -0.3565 0.01145 0.00457 0.0097 0.9140 0.5401
-2.500 -0.3212 0.01123 0.00434 0.0081 0.9097 0.5580
-2.250 -0.2959 0.01105 0.00416 0.0086 0.9002 0.5747
-2.000 -0.2597 0.01082 0.00395 0.0068 0.8951 0.5919
-1.750 -0.2331 0.01063 0.00381 0.0071 0.8848 0.6081
-1.500 -0.2015 0.01042 0.00364 0.0063 0.8762 0.6287
-1.250 -0.1688 0.01016 0.00352 0.0054 0.8674 0.6599
-1.000 -0.1389 0.00995 0.00348 0.0052 0.8560 0.6969
-0.750 -0.1059 0.00980 0.00345 0.0043 0.8443 0.7328
-0.500 -0.0710 0.00971 0.00341 0.0029 0.8315 0.7606
-0.250 -0.0360 0.00965 0.00337 0.0016 0.8169 0.7820
0.000 0.0000 0.00963 0.00336 0.0000 0.8004 0.8004
0.250 0.0360 0.00965 0.00337 -0.0016 0.7821 0.8170
0.500 0.0710 0.00971 0.00341 -0.0029 0.7608 0.8316
0.750 0.1059 0.00981 0.00345 -0.0043 0.7326 0.8444
1.000 0.1391 0.00995 0.00349 -0.0052 0.6978 0.8561
1.250 0.1688 0.01016 0.00352 -0.0054 0.6597 0.8673
1.500 0.2014 0.01042 0.00364 -0.0063 0.6285 0.8762
1.750 0.2332 0.01063 0.00381 -0.0071 0.6082 0.8848
2.000 0.2596 0.01081 0.00395 -0.0068 0.5919 0.8951
2.250 0.2959 0.01105 0.00416 -0.0086 0.5746 0.9003
2.500 0.3211 0.01122 0.00434 -0.0080 0.5585 0.9096
2.750 0.3565 0.01145 0.00457 -0.0097 0.5400 0.9140
3.000 0.3807 0.01163 0.00476 -0.0089 0.5235 0.9229
3.250 0.4145 0.01189 0.00502 -0.0102 0.5006 0.9265
3.500 0.4340 0.01227 0.00517 -0.0086 0.4379 0.9349
3.750 0.4595 0.01291 0.00540 -0.0085 0.3468 0.9396
4.000 0.4782 0.01360 0.00572 -0.0070 0.2666 0.9476
4.250 0.5014 0.01480 0.00629 -0.0070 0.1480 0.9523
4.500 0.5174 0.01622 0.00711 -0.0054 0.0267 0.9596
4.750 0.5482 0.01671 0.00774 -0.0063 0.0214 0.9638
5.000 0.5748 0.01732 0.00850 -0.0062 0.0186 0.9695
5.250 0.6030 0.01816 0.00955 -0.0066 0.0160 0.9739
5.500 0.6315 0.01878 0.01033 -0.0072 0.0148 0.9792
5.750 0.6606 0.01970 0.01139 -0.0079 0.0137 0.9846
6.000 0.6895 0.02078 0.01257 -0.0088 0.0129 0.9897
6.250 0.7179 0.02198 0.01384 -0.0095 0.0124 0.9948
6.500 0.7488 0.02314 0.01505 -0.0110 0.0111 0.9988
6.750 0.7652 0.02417 0.01612 -0.0094 0.0105 1.0000
7.000 0.7741 0.02564 0.01757 -0.0064 0.0097 1.0000
7.250 0.7882 0.02721 0.01919 -0.0041 0.0095 1.0000
7.500 0.8059 0.02942 0.02150 -0.0026 0.0093 1.0000
7.750 0.8205 0.03133 0.02361 -0.0004 0.0091 1.0000
8.000 0.8317 0.03280 0.02527 0.0024 0.0090 1.0000
8.250 0.8414 0.03438 0.02704 0.0053 0.0090 1.0000
8.500 0.8488 0.03606 0.02893 0.0086 0.0089 1.0000
8.750 0.8539 0.03803 0.03113 0.0121 0.0089 1.0000
9.000 0.8573 0.04000 0.03330 0.0156 0.0090 1.0000
9.250 0.8568 0.04221 0.03575 0.0197 0.0090 1.0000
9.500 0.8549 0.04502 0.03877 0.0236 0.0091 1.0000
9.750 0.8479 0.04578 0.03974 0.0286 0.0089 1.0000
10.250 0.8242 0.04850 0.04280 0.0394 0.0087 1.0000
10.500 0.8115 0.05033 0.04480 0.0438 0.0087 1.0000
10.750 0.8014 0.05127 0.04593 0.0476 0.0082 1.0000
11.000 0.7901 0.05312 0.04798 0.0505 0.0078 1.0000
11.250 0.7710 0.05736 0.05236 0.0524 0.0085 1.0000
11.500 0.7582 0.05977 0.05496 0.0535 0.0082 1.0000
11.750 0.7433 0.06311 0.05847 0.0537 0.0080 1.0000
13.500 0.5371 0.09166 0.08796 0.0436 0.0097 1.0000
13.750 0.5137 0.09910 0.09553 0.0393 0.0099 1.0000
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