S5010 (s5010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 500,000 Max Cl/Cd: 86.25 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5010-il-500000.txt Download as CSV file: xf-s5010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S5010
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5488 0.08332 0.08147 0.0100 1.0000 0.0177
-8.000 -0.5533 0.07850 0.07670 0.0062 1.0000 0.0179
-7.750 -0.5585 0.07292 0.07102 0.0000 0.9031 0.0179
-7.500 -0.5645 0.06763 0.06555 -0.0033 0.8675 0.0180
-7.250 -0.5654 0.06180 0.05953 -0.0063 0.8472 0.0184
-6.750 -0.5516 0.04948 0.04649 -0.0095 0.8196 0.0201
-6.500 -0.5423 0.04517 0.04179 -0.0093 0.8085 0.0201
-6.250 -0.5418 0.03722 0.03351 -0.0094 0.7992 0.0211
-6.000 -0.5230 0.03514 0.03132 -0.0092 0.7885 0.0217
-5.750 -0.5033 0.03308 0.02907 -0.0088 0.7790 0.0227
-5.500 -0.4825 0.03062 0.02629 -0.0081 0.7700 0.0245
-5.250 -0.4648 0.02320 0.01794 -0.0055 0.7624 0.0188
-5.000 -0.4403 0.02147 0.01582 -0.0046 0.7543 0.0195
-4.750 -0.4160 0.01891 0.01289 -0.0037 0.7454 0.0193
-4.500 -0.3901 0.01735 0.01103 -0.0029 0.7374 0.0196
-4.250 -0.3631 0.01657 0.01003 -0.0024 0.7287 0.0202
-4.000 -0.3384 0.01426 0.00753 -0.0016 0.7209 0.0212
-3.750 -0.3122 0.01356 0.00679 -0.0013 0.7127 0.0230
-3.500 -0.2853 0.01298 0.00614 -0.0009 0.7043 0.0246
-3.250 -0.2587 0.01236 0.00541 -0.0004 0.6967 0.0256
-3.000 -0.2317 0.01186 0.00484 0.0000 0.6880 0.0267
-2.750 -0.2059 0.01113 0.00401 0.0006 0.6806 0.0288
-2.500 -0.1788 0.01068 0.00352 0.0009 0.6720 0.0311
-2.250 -0.1515 0.01038 0.00314 0.0012 0.6644 0.0334
-2.000 -0.1237 0.01013 0.00283 0.0014 0.6558 0.0360
-1.750 -0.0963 0.00980 0.00248 0.0017 0.6479 0.0463
-1.500 -0.0715 0.00889 0.00215 0.0021 0.6398 0.1965
-1.250 -0.0473 0.00806 0.00198 0.0025 0.6317 0.3899
-1.000 -0.0239 0.00738 0.00187 0.0032 0.6238 0.5614
-0.750 -0.0029 0.00668 0.00183 0.0049 0.6154 0.7406
-0.500 0.0204 0.00627 0.00183 0.0066 0.6076 0.8774
-0.250 0.0766 0.00631 0.00192 0.0013 0.5970 0.9638
0.000 0.1368 0.00644 0.00192 -0.0052 0.5864 0.9911
0.250 0.1875 0.00647 0.00183 -0.0100 0.5761 1.0000
0.500 0.2131 0.00648 0.00176 -0.0095 0.5668 1.0000
0.750 0.2389 0.00650 0.00171 -0.0091 0.5574 1.0000
1.000 0.2647 0.00655 0.00167 -0.0086 0.5482 1.0000
1.250 0.2907 0.00658 0.00165 -0.0082 0.5384 1.0000
1.500 0.3169 0.00663 0.00164 -0.0078 0.5285 1.0000
1.750 0.3431 0.00670 0.00164 -0.0074 0.5188 1.0000
2.000 0.3694 0.00676 0.00165 -0.0070 0.5084 1.0000
2.250 0.3958 0.00683 0.00168 -0.0066 0.4979 1.0000
2.500 0.4222 0.00691 0.00171 -0.0063 0.4873 1.0000
2.750 0.4485 0.00701 0.00175 -0.0059 0.4765 1.0000
3.000 0.4751 0.00710 0.00180 -0.0056 0.4649 1.0000
3.250 0.5016 0.00720 0.00187 -0.0053 0.4529 1.0000
3.500 0.5281 0.00731 0.00194 -0.0050 0.4406 1.0000
3.750 0.5546 0.00743 0.00203 -0.0047 0.4278 1.0000
4.000 0.5811 0.00757 0.00213 -0.0045 0.4146 1.0000
4.250 0.6075 0.00772 0.00224 -0.0042 0.4010 1.0000
4.500 0.6340 0.00788 0.00237 -0.0039 0.3868 1.0000
4.750 0.6604 0.00805 0.00250 -0.0037 0.3722 1.0000
5.000 0.6867 0.00824 0.00266 -0.0035 0.3566 1.0000
5.250 0.7130 0.00844 0.00283 -0.0032 0.3412 1.0000
5.500 0.7392 0.00867 0.00301 -0.0030 0.3249 1.0000
5.750 0.7653 0.00892 0.00322 -0.0028 0.3083 1.0000
6.000 0.7911 0.00919 0.00345 -0.0025 0.2917 1.0000
6.250 0.8169 0.00948 0.00369 -0.0023 0.2750 1.0000
6.500 0.8427 0.00977 0.00395 -0.0021 0.2585 1.0000
6.750 0.8683 0.01009 0.00424 -0.0018 0.2420 1.0000
7.000 0.8938 0.01042 0.00454 -0.0016 0.2262 1.0000
7.250 0.9191 0.01078 0.00486 -0.0014 0.2101 1.0000
7.500 0.9442 0.01115 0.00521 -0.0012 0.1952 1.0000
7.750 0.9691 0.01156 0.00559 -0.0009 0.1799 1.0000
8.000 0.9938 0.01198 0.00598 -0.0007 0.1656 1.0000
8.250 1.0183 0.01243 0.00640 -0.0004 0.1515 1.0000
8.500 1.0425 0.01290 0.00685 -0.0001 0.1380 1.0000
8.750 1.0665 0.01339 0.00733 0.0002 0.1254 1.0000
9.000 1.0901 0.01389 0.00783 0.0005 0.1134 1.0000
9.250 1.1134 0.01444 0.00836 0.0008 0.1018 1.0000
9.500 1.1361 0.01501 0.00892 0.0012 0.0900 1.0000
9.750 1.1582 0.01563 0.00951 0.0015 0.0785 1.0000
10.000 1.1798 0.01628 0.01016 0.0020 0.0684 1.0000
10.250 1.2003 0.01703 0.01088 0.0025 0.0597 1.0000
10.500 1.2211 0.01768 0.01155 0.0030 0.0526 1.0000
10.750 1.2409 0.01840 0.01230 0.0036 0.0461 1.0000
11.000 1.2580 0.01933 0.01321 0.0043 0.0389 1.0000
11.250 1.2767 0.02003 0.01397 0.0050 0.0340 1.0000
11.500 1.2917 0.02101 0.01497 0.0059 0.0282 1.0000
11.750 1.3026 0.02223 0.01620 0.0072 0.0220 1.0000
12.000 1.3059 0.02372 0.01772 0.0091 0.0172 1.0000
12.250 1.3056 0.02533 0.01940 0.0109 0.0143 1.0000
12.500 1.2996 0.02781 0.02195 0.0120 0.0121 1.0000
12.750 1.3025 0.02981 0.02407 0.0125 0.0115 1.0000
13.000 1.3027 0.03220 0.02657 0.0127 0.0104 1.0000
13.250 1.3028 0.03474 0.02921 0.0125 0.0099 1.0000
13.500 1.2959 0.03818 0.03274 0.0121 0.0092 1.0000
13.750 1.2835 0.04242 0.03712 0.0111 0.0088 1.0000
14.000 1.2783 0.04599 0.04080 0.0101 0.0086 1.0000
14.250 1.2700 0.05004 0.04497 0.0089 0.0086 1.0000
14.500 1.2685 0.05337 0.04843 0.0078 0.0080 1.0000
14.750 1.2620 0.05744 0.05262 0.0063 0.0079 1.0000
15.000 1.2535 0.06192 0.05721 0.0046 0.0078 1.0000
15.250 1.2454 0.06659 0.06200 0.0026 0.0075 1.0000
15.500 1.2343 0.07183 0.06737 0.0004 0.0076 1.0000
15.750 1.2226 0.07739 0.07304 -0.0022 0.0072 1.0000
16.000 1.2141 0.08258 0.07833 -0.0046 0.0072 1.0000
16.250 1.2032 0.08830 0.08416 -0.0073 0.0070 1.0000
16.500 1.1934 0.09393 0.08989 -0.0100 0.0070 1.0000
16.750 1.1826 0.09990 0.09598 -0.0129 0.0069 1.0000
17.000 1.1719 0.10592 0.10211 -0.0159 0.0069 1.0000
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Polar data table (+)
Polar graphs
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