RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 200,000 Max Cl/Cd: 36.31 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf30md-il-200000-n5.txt Download as CSV file: xf-raf30md-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6978 0.08623 0.08279 -0.0012 1.0000 0.0103
-9.750 -0.7257 0.07102 0.06765 -0.0125 1.0000 0.0097
-9.500 -0.7610 0.05940 0.05584 -0.0202 1.0000 0.0092
-9.250 -0.7824 0.05452 0.05077 -0.0201 1.0000 0.0091
-9.000 -0.7953 0.04963 0.04561 -0.0194 1.0000 0.0091
-8.750 -0.8027 0.04496 0.04060 -0.0183 1.0000 0.0091
-8.500 -0.8037 0.04066 0.03592 -0.0169 1.0000 0.0093
-8.250 -0.7930 0.03874 0.03381 -0.0161 1.0000 0.0098
-8.000 -0.7815 0.03632 0.03111 -0.0149 1.0000 0.0103
-7.750 -0.7666 0.03441 0.02894 -0.0139 1.0000 0.0112
-7.500 -0.7538 0.03120 0.02530 -0.0123 1.0000 0.0117
-7.250 -0.7386 0.02818 0.02182 -0.0107 1.0000 0.0122
-7.000 -0.7206 0.02566 0.01890 -0.0093 1.0000 0.0128
-6.750 -0.7007 0.02354 0.01643 -0.0080 1.0000 0.0135
-6.500 -0.6786 0.02227 0.01489 -0.0069 1.0000 0.0144
-6.250 -0.6596 0.02000 0.01242 -0.0057 1.0000 0.0164
-6.000 -0.6377 0.01890 0.01122 -0.0047 1.0000 0.0182
-5.750 -0.6158 0.01778 0.00993 -0.0036 1.0000 0.0204
-5.500 -0.5931 0.01699 0.00900 -0.0025 1.0000 0.0239
-5.250 -0.5701 0.01633 0.00823 -0.0016 1.0000 0.0264
-5.000 -0.5503 0.01518 0.00706 -0.0003 1.0000 0.0307
-4.750 -0.5276 0.01465 0.00644 0.0006 1.0000 0.0357
-4.500 -0.5061 0.01393 0.00562 0.0018 1.0000 0.0398
-4.250 -0.4835 0.01343 0.00507 0.0027 1.0000 0.0451
-4.000 -0.4605 0.01302 0.00457 0.0036 1.0000 0.0490
-3.750 -0.4380 0.01251 0.00405 0.0046 1.0000 0.0565
-3.500 -0.4154 0.01204 0.00361 0.0056 1.0000 0.0721
-3.250 -0.3939 0.01142 0.00323 0.0066 1.0000 0.1276
-3.000 -0.3732 0.01074 0.00290 0.0076 1.0000 0.2110
-2.750 -0.3529 0.01009 0.00266 0.0087 1.0000 0.3103
-2.500 -0.3331 0.00950 0.00249 0.0100 1.0000 0.4120
-2.250 -0.3127 0.00910 0.00237 0.0113 1.0000 0.4900
-2.000 -0.2922 0.00880 0.00232 0.0127 1.0000 0.5574
-1.750 -0.2602 0.00847 0.00233 0.0118 0.9930 0.6412
-1.500 -0.2285 0.00816 0.00238 0.0112 0.9849 0.7318
-1.250 -0.1956 0.00798 0.00243 0.0106 0.9765 0.7973
-1.000 -0.1597 0.00789 0.00243 0.0092 0.9681 0.8314
-0.750 -0.1224 0.00785 0.00241 0.0075 0.9581 0.8567
-0.500 -0.0837 0.00782 0.00240 0.0054 0.9469 0.8805
-0.250 -0.0423 0.00781 0.00240 0.0028 0.9343 0.9008
0.000 0.0000 0.00781 0.00241 0.0000 0.9189 0.9189
0.250 0.0424 0.00781 0.00241 -0.0028 0.9008 0.9344
0.500 0.0838 0.00782 0.00240 -0.0054 0.8803 0.9468
0.750 0.1224 0.00785 0.00241 -0.0075 0.8567 0.9581
1.000 0.1597 0.00790 0.00243 -0.0092 0.8314 0.9681
1.250 0.1956 0.00798 0.00243 -0.0106 0.7972 0.9765
1.500 0.2285 0.00816 0.00239 -0.0112 0.7323 0.9848
1.750 0.2604 0.00846 0.00233 -0.0118 0.6451 0.9929
2.000 0.2924 0.00879 0.00233 -0.0128 0.5588 1.0000
2.250 0.3128 0.00910 0.00237 -0.0113 0.4883 1.0000
2.750 0.3531 0.01009 0.00266 -0.0087 0.3111 1.0000
3.000 0.3733 0.01075 0.00291 -0.0076 0.2085 1.0000
3.250 0.3941 0.01142 0.00323 -0.0066 0.1285 1.0000
3.500 0.4155 0.01204 0.00363 -0.0056 0.0719 1.0000
3.750 0.4381 0.01251 0.00405 -0.0046 0.0565 1.0000
4.000 0.4606 0.01302 0.00457 -0.0036 0.0490 1.0000
4.250 0.4837 0.01343 0.00507 -0.0027 0.0451 1.0000
4.500 0.5062 0.01394 0.00563 -0.0018 0.0398 1.0000
4.750 0.5277 0.01465 0.00644 -0.0007 0.0357 1.0000
5.000 0.5504 0.01519 0.00707 0.0003 0.0307 1.0000
5.250 0.5700 0.01637 0.00826 0.0016 0.0263 1.0000
5.500 0.5931 0.01700 0.00902 0.0025 0.0240 1.0000
5.750 0.6158 0.01778 0.00993 0.0036 0.0203 1.0000
6.000 0.6377 0.01890 0.01122 0.0047 0.0183 1.0000
6.250 0.6596 0.02001 0.01244 0.0057 0.0165 1.0000
6.500 0.6784 0.02229 0.01491 0.0069 0.0144 1.0000
6.750 0.7006 0.02357 0.01645 0.0080 0.0135 1.0000
7.000 0.7205 0.02565 0.01888 0.0093 0.0128 1.0000
7.250 0.7385 0.02817 0.02181 0.0107 0.0122 1.0000
7.500 0.7536 0.03122 0.02532 0.0124 0.0117 1.0000
7.750 0.7662 0.03447 0.02901 0.0140 0.0113 1.0000
8.000 0.7797 0.03678 0.03162 0.0151 0.0105 1.0000
8.250 0.7910 0.03925 0.03437 0.0163 0.0099 1.0000
8.500 0.8020 0.04109 0.03640 0.0171 0.0094 1.0000
8.750 0.8026 0.04490 0.04054 0.0184 0.0091 1.0000
9.000 0.7955 0.04960 0.04558 0.0195 0.0091 1.0000
9.250 0.7821 0.05443 0.05068 0.0201 0.0091 1.0000
9.500 0.7595 0.05980 0.05624 0.0202 0.0093 1.0000
9.750 0.7270 0.07047 0.06709 0.0129 0.0096 1.0000
10.000 0.6947 0.08721 0.08377 0.0006 0.0107 1.0000
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Polar data table (+)
Polar graphs
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