RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 100,000 Max Cl/Cd: 31.04 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf30md-il-100000-n5.txt Download as CSV file: xf-raf30md-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 MOD AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6800 0.08518 0.08035 -0.0040 1.0000 0.0212
-9.250 -0.6904 0.07722 0.07244 -0.0104 1.0000 0.0209
-9.000 -0.7057 0.07052 0.06571 -0.0157 1.0000 0.0205
-8.750 -0.7223 0.06545 0.06054 -0.0171 1.0000 0.0202
-8.500 -0.7333 0.06036 0.05528 -0.0179 1.0000 0.0200
-8.250 -0.7398 0.05539 0.05005 -0.0180 1.0000 0.0200
-8.000 -0.7417 0.05059 0.04492 -0.0174 1.0000 0.0199
-7.750 -0.7391 0.04607 0.04000 -0.0164 1.0000 0.0202
-7.500 -0.7319 0.04211 0.03559 -0.0152 1.0000 0.0213
-7.250 -0.7212 0.03844 0.03139 -0.0138 1.0000 0.0227
-7.000 -0.7072 0.03497 0.02736 -0.0122 1.0000 0.0236
-6.750 -0.6903 0.03181 0.02363 -0.0107 1.0000 0.0244
-6.500 -0.6703 0.02923 0.02054 -0.0093 1.0000 0.0254
-6.250 -0.6503 0.02676 0.01779 -0.0082 1.0000 0.0276
-6.000 -0.6290 0.02514 0.01599 -0.0074 1.0000 0.0309
-5.750 -0.6063 0.02334 0.01396 -0.0063 1.0000 0.0336
-5.500 -0.5837 0.02186 0.01227 -0.0051 1.0000 0.0377
-5.250 -0.5631 0.02045 0.01087 -0.0041 1.0000 0.0429
-5.000 -0.5410 0.01943 0.00968 -0.0029 1.0000 0.0484
-4.750 -0.5210 0.01829 0.00856 -0.0017 1.0000 0.0560
-4.500 -0.4991 0.01752 0.00761 -0.0005 1.0000 0.0628
-4.250 -0.4777 0.01671 0.00679 0.0006 1.0000 0.0733
-4.000 -0.4561 0.01592 0.00600 0.0018 1.0000 0.0874
-3.750 -0.4356 0.01494 0.00527 0.0030 1.0000 0.1364
-3.500 -0.4168 0.01383 0.00470 0.0042 1.0000 0.2524
-3.250 -0.3977 0.01297 0.00434 0.0056 1.0000 0.3723
-3.000 -0.3795 0.01222 0.00416 0.0075 1.0000 0.5024
-2.750 -0.3606 0.01173 0.00410 0.0096 1.0000 0.6126
-2.500 -0.3408 0.01141 0.00411 0.0120 1.0000 0.7049
-2.250 -0.3193 0.01123 0.00407 0.0141 1.0000 0.7713
-2.000 -0.2952 0.01113 0.00405 0.0156 1.0000 0.8219
-1.750 -0.2655 0.01111 0.00404 0.0159 1.0000 0.8649
-1.500 -0.2312 0.01111 0.00396 0.0149 1.0000 0.8945
-1.250 -0.1920 0.01114 0.00391 0.0127 1.0000 0.9196
-1.000 -0.1505 0.01117 0.00386 0.0099 1.0000 0.9420
-0.750 -0.1077 0.01118 0.00380 0.0067 1.0000 0.9623
-0.500 -0.0627 0.01117 0.00374 0.0029 1.0000 0.9799
-0.250 -0.0169 0.01114 0.00367 -0.0013 1.0000 0.9966
0.000 0.0000 0.01111 0.00364 0.0000 1.0000 1.0000
0.250 0.0169 0.01114 0.00367 0.0013 0.9966 1.0000
0.500 0.0628 0.01117 0.00374 -0.0029 0.9799 1.0000
0.750 0.1076 0.01118 0.00380 -0.0067 0.9623 1.0000
1.000 0.1506 0.01117 0.00386 -0.0099 0.9419 1.0000
1.250 0.1920 0.01114 0.00391 -0.0128 0.9196 1.0000
1.500 0.2313 0.01111 0.00396 -0.0149 0.8945 1.0000
1.750 0.2656 0.01111 0.00404 -0.0160 0.8650 1.0000
2.000 0.2953 0.01113 0.00405 -0.0156 0.8217 1.0000
2.250 0.3194 0.01123 0.00407 -0.0141 0.7709 1.0000
2.500 0.3410 0.01141 0.00411 -0.0120 0.7051 1.0000
2.750 0.3608 0.01173 0.00411 -0.0097 0.6134 1.0000
3.000 0.3796 0.01223 0.00416 -0.0075 0.5008 1.0000
3.250 0.3978 0.01297 0.00434 -0.0056 0.3730 1.0000
3.500 0.4169 0.01384 0.00470 -0.0042 0.2521 1.0000
3.750 0.4357 0.01494 0.00528 -0.0030 0.1364 1.0000
4.000 0.4562 0.01592 0.00600 -0.0018 0.0873 1.0000
4.250 0.4778 0.01671 0.00679 -0.0006 0.0733 1.0000
4.500 0.4991 0.01752 0.00761 0.0005 0.0626 1.0000
4.750 0.5210 0.01829 0.00857 0.0017 0.0559 1.0000
5.000 0.5411 0.01942 0.00967 0.0029 0.0484 1.0000
5.250 0.5631 0.02045 0.01087 0.0041 0.0429 1.0000
5.500 0.5838 0.02184 0.01225 0.0051 0.0378 1.0000
5.750 0.6063 0.02335 0.01397 0.0063 0.0336 1.0000
6.000 0.6290 0.02514 0.01599 0.0074 0.0309 1.0000
6.250 0.6502 0.02675 0.01778 0.0082 0.0276 1.0000
6.500 0.6703 0.02923 0.02053 0.0093 0.0254 1.0000
6.750 0.6901 0.03182 0.02365 0.0107 0.0244 1.0000
7.000 0.7071 0.03495 0.02733 0.0123 0.0236 1.0000
7.250 0.7210 0.03843 0.03138 0.0138 0.0226 1.0000
7.500 0.7316 0.04211 0.03559 0.0153 0.0213 1.0000
7.750 0.7389 0.04606 0.03999 0.0165 0.0203 1.0000
8.000 0.7415 0.05055 0.04488 0.0175 0.0199 1.0000
8.250 0.7397 0.05533 0.04999 0.0180 0.0200 1.0000
8.500 0.7331 0.06032 0.05524 0.0180 0.0200 1.0000
8.750 0.7222 0.06540 0.06049 0.0172 0.0203 1.0000
9.000 0.7059 0.07043 0.06561 0.0158 0.0205 1.0000
9.250 0.6901 0.07729 0.07251 0.0104 0.0209 1.0000
9.500 0.6802 0.08510 0.08027 0.0040 0.0213 1.0000
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Polar data table (+)
Polar graphs
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