NASA RC(5)-10 AIRFOIL (rc510-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA RC(5)-10 AIRFOIL (rc510-il) Reynolds number: 500,000 Max Cl/Cd: 75.73 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc510-il-500000-n5.txt Download as CSV file: xf-rc510-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA RC(5)-10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6012 0.08377 0.08125 0.0026 0.8179 0.0120
-8.750 -0.6193 0.07511 0.07253 -0.0065 0.8080 0.0119
-8.500 -0.6310 0.06704 0.06432 -0.0122 0.8006 0.0119
-8.250 -0.7268 0.02928 0.02482 -0.0164 0.7965 0.0121
-8.000 -0.7092 0.02689 0.02209 -0.0155 0.7906 0.0124
-7.750 -0.6895 0.02484 0.01972 -0.0148 0.7847 0.0127
-7.500 -0.6689 0.02298 0.01754 -0.0140 0.7794 0.0130
-7.250 -0.6472 0.02125 0.01549 -0.0132 0.7747 0.0132
-7.000 -0.6240 0.01983 0.01380 -0.0125 0.7696 0.0134
-6.750 -0.6000 0.01866 0.01239 -0.0119 0.7645 0.0137
-6.500 -0.5752 0.01768 0.01120 -0.0114 0.7599 0.0140
-6.250 -0.5497 0.01682 0.01017 -0.0110 0.7550 0.0142
-6.000 -0.5240 0.01609 0.00929 -0.0106 0.7504 0.0144
-5.750 -0.4980 0.01547 0.00853 -0.0102 0.7464 0.0146
-5.500 -0.4727 0.01460 0.00757 -0.0097 0.7420 0.0150
-5.250 -0.4466 0.01402 0.00693 -0.0094 0.7373 0.0154
-5.000 -0.4203 0.01356 0.00641 -0.0091 0.7329 0.0158
-4.750 -0.3937 0.01314 0.00592 -0.0088 0.7287 0.0162
-4.500 -0.3667 0.01276 0.00551 -0.0085 0.7242 0.0169
-4.250 -0.3398 0.01241 0.00511 -0.0083 0.7200 0.0177
-4.000 -0.3129 0.01209 0.00471 -0.0080 0.7162 0.0183
-3.750 -0.2861 0.01170 0.00429 -0.0077 0.7120 0.0190
-3.500 -0.2591 0.01135 0.00392 -0.0075 0.7074 0.0200
-3.250 -0.2319 0.01108 0.00363 -0.0072 0.7031 0.0212
-3.000 -0.2046 0.01085 0.00334 -0.0070 0.6993 0.0228
-2.750 -0.1772 0.01059 0.00309 -0.0069 0.6951 0.0251
-2.500 -0.1496 0.01038 0.00287 -0.0067 0.6909 0.0289
-2.250 -0.1222 0.01017 0.00267 -0.0065 0.6869 0.0355
-2.000 -0.0947 0.00998 0.00252 -0.0064 0.6830 0.0442
-1.750 -0.0668 0.00982 0.00239 -0.0063 0.6784 0.0539
-1.500 -0.0391 0.00968 0.00226 -0.0062 0.6723 0.0641
-1.250 -0.0114 0.00954 0.00214 -0.0061 0.6639 0.0763
-1.000 0.0162 0.00941 0.00203 -0.0060 0.6550 0.0929
-0.750 0.0441 0.00929 0.00195 -0.0060 0.6466 0.1085
-0.500 0.0719 0.00919 0.00185 -0.0059 0.6388 0.1239
-0.250 0.0999 0.00907 0.00178 -0.0058 0.6306 0.1427
0.250 0.1458 0.00747 0.00154 -0.0045 0.6144 0.5815
0.500 0.1690 0.00704 0.00149 -0.0035 0.6055 0.6985
0.750 0.1906 0.00658 0.00150 -0.0017 0.5961 0.8246
1.000 0.2223 0.00649 0.00161 -0.0020 0.5834 0.9207
1.250 0.2620 0.00659 0.00166 -0.0044 0.5672 0.9494
1.500 0.3006 0.00671 0.00170 -0.0065 0.5520 0.9642
1.750 0.3357 0.00684 0.00174 -0.0080 0.5327 0.9742
2.000 0.3713 0.00701 0.00179 -0.0097 0.5028 0.9820
2.250 0.4074 0.00732 0.00186 -0.0116 0.4455 0.9877
2.500 0.4432 0.00800 0.00208 -0.0138 0.3467 0.9933
2.750 0.4818 0.00849 0.00229 -0.0166 0.2909 0.9971
3.000 0.5152 0.00878 0.00244 -0.0181 0.2633 0.9992
3.250 0.5442 0.00900 0.00256 -0.0185 0.2452 1.0000
3.500 0.5696 0.00921 0.00269 -0.0182 0.2302 1.0000
3.750 0.5948 0.00942 0.00283 -0.0178 0.2174 1.0000
4.000 0.6201 0.00960 0.00296 -0.0174 0.2074 1.0000
4.250 0.6452 0.00978 0.00311 -0.0169 0.1992 1.0000
4.750 0.6952 0.01017 0.00344 -0.0160 0.1829 1.0000
5.000 0.7200 0.01039 0.00362 -0.0156 0.1761 1.0000
5.250 0.7449 0.01058 0.00381 -0.0151 0.1704 1.0000
5.500 0.7696 0.01080 0.00400 -0.0146 0.1637 1.0000
5.750 0.7943 0.01102 0.00421 -0.0141 0.1581 1.0000
6.000 0.8189 0.01123 0.00442 -0.0136 0.1527 1.0000
6.250 0.8432 0.01150 0.00467 -0.0131 0.1466 1.0000
6.500 0.8678 0.01172 0.00490 -0.0126 0.1421 1.0000
6.750 0.8922 0.01196 0.00515 -0.0121 0.1373 1.0000
7.000 0.9160 0.01226 0.00543 -0.0115 0.1320 1.0000
7.250 0.9404 0.01249 0.00570 -0.0110 0.1274 1.0000
7.500 0.9643 0.01277 0.00599 -0.0105 0.1226 1.0000
7.750 0.9878 0.01309 0.00630 -0.0099 0.1176 1.0000
8.000 1.0117 0.01336 0.00660 -0.0093 0.1123 1.0000
8.250 1.0349 0.01371 0.00694 -0.0087 0.1067 1.0000
8.500 1.0584 0.01401 0.00728 -0.0082 0.1023 1.0000
8.750 1.0816 0.01436 0.00763 -0.0076 0.0969 1.0000
9.000 1.1043 0.01475 0.00803 -0.0070 0.0919 1.0000
9.250 1.1274 0.01510 0.00842 -0.0064 0.0866 1.0000
9.500 1.1494 0.01557 0.00886 -0.0058 0.0805 1.0000
9.750 1.1720 0.01596 0.00929 -0.0052 0.0752 1.0000
10.000 1.1932 0.01648 0.00980 -0.0046 0.0686 1.0000
10.250 1.2147 0.01697 0.01030 -0.0039 0.0622 1.0000
10.500 1.2350 0.01755 0.01087 -0.0032 0.0555 1.0000
10.750 1.2546 0.01819 0.01149 -0.0024 0.0491 1.0000
11.000 1.2745 0.01878 0.01212 -0.0016 0.0442 1.0000
11.250 1.2927 0.01950 0.01284 -0.0007 0.0389 1.0000
11.500 1.3106 0.02020 0.01357 0.0002 0.0342 1.0000
11.750 1.3273 0.02099 0.01438 0.0012 0.0304 1.0000
12.000 1.3431 0.02179 0.01522 0.0023 0.0270 1.0000
12.250 1.3559 0.02267 0.01614 0.0038 0.0243 1.0000
12.500 1.3677 0.02359 0.01712 0.0052 0.0218 1.0000
12.750 1.3777 0.02473 0.01831 0.0065 0.0195 1.0000
13.000 1.3888 0.02586 0.01953 0.0075 0.0176 1.0000
13.250 1.3975 0.02727 0.02098 0.0084 0.0157 1.0000
13.500 1.4068 0.02867 0.02247 0.0091 0.0142 1.0000
13.750 1.4145 0.03026 0.02413 0.0098 0.0129 1.0000
14.000 1.4201 0.03209 0.02603 0.0104 0.0117 1.0000
14.250 1.4266 0.03386 0.02792 0.0109 0.0109 1.0000
14.500 1.4310 0.03589 0.03004 0.0113 0.0102 1.0000
14.750 1.4332 0.03818 0.03244 0.0115 0.0096 1.0000
15.000 1.4329 0.04081 0.03518 0.0117 0.0091 1.0000
15.250 1.4326 0.04351 0.03800 0.0116 0.0087 1.0000
15.500 1.4311 0.04644 0.04105 0.0113 0.0084 1.0000
15.750 1.4273 0.04972 0.04446 0.0108 0.0082 1.0000
16.000 1.4214 0.05340 0.04828 0.0101 0.0079 1.0000
16.250 1.4128 0.05756 0.05257 0.0089 0.0077 1.0000
16.500 1.4017 0.06232 0.05748 0.0073 0.0076 1.0000
16.750 1.3880 0.06782 0.06313 0.0051 0.0075 1.0000
17.000 1.3705 0.07425 0.06972 0.0023 0.0074 1.0000
17.250 1.3490 0.08183 0.07748 -0.0014 0.0074 1.0000
17.500 1.3226 0.09064 0.08647 -0.0057 0.0074 1.0000
17.750 1.2924 0.10037 0.09638 -0.0105 0.0075 1.0000
18.000 1.2606 0.11032 0.10650 -0.0153 0.0077 1.0000
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