RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 500,000 Max Cl/Cd: 71.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1495-il-500000-n5.txt Download as CSV file: xf-rg1495-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9.5% 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8887 0.05150 0.04869 -0.0520 1.0000 0.0066
-12.750 -0.9183 0.04291 0.03986 -0.0594 1.0000 0.0066
-12.500 -0.9377 0.03872 0.03545 -0.0599 1.0000 0.0065
-12.250 -0.9533 0.03604 0.03262 -0.0578 1.0000 0.0067
-12.000 -0.9654 0.03388 0.03029 -0.0542 1.0000 0.0068
-11.750 -0.9660 0.03199 0.02823 -0.0517 1.0000 0.0069
-11.500 -0.9591 0.03064 0.02676 -0.0497 1.0000 0.0070
-11.250 -0.9515 0.02919 0.02515 -0.0477 1.0000 0.0072
-11.000 -0.9407 0.02799 0.02383 -0.0459 1.0000 0.0073
-10.750 -0.9281 0.02691 0.02262 -0.0441 1.0000 0.0076
-10.500 -0.9160 0.02567 0.02122 -0.0423 1.0000 0.0078
-10.250 -0.9019 0.02462 0.02001 -0.0405 1.0000 0.0082
-10.000 -0.8874 0.02354 0.01876 -0.0388 1.0000 0.0086
-9.750 -0.8724 0.02244 0.01746 -0.0370 1.0000 0.0090
-9.500 -0.8563 0.02147 0.01631 -0.0353 1.0000 0.0093
-9.250 -0.8409 0.02042 0.01514 -0.0336 1.0000 0.0097
-9.000 -0.8227 0.01979 0.01445 -0.0322 1.0000 0.0101
-8.750 -0.8041 0.01919 0.01378 -0.0308 1.0000 0.0105
-8.500 -0.7853 0.01862 0.01312 -0.0294 1.0000 0.0110
-8.250 -0.7574 0.01787 0.01224 -0.0298 0.9986 0.0117
-8.000 -0.7267 0.01715 0.01138 -0.0309 0.9966 0.0124
-7.750 -0.6950 0.01658 0.01068 -0.0320 0.9947 0.0131
-7.500 -0.6661 0.01567 0.00968 -0.0327 0.9924 0.0139
-7.250 -0.6358 0.01518 0.00916 -0.0336 0.9896 0.0148
-7.000 -0.6045 0.01466 0.00856 -0.0346 0.9870 0.0157
-6.750 -0.5723 0.01411 0.00793 -0.0358 0.9847 0.0166
-6.500 -0.5400 0.01367 0.00742 -0.0369 0.9823 0.0175
-6.250 -0.5117 0.01319 0.00687 -0.0371 0.9778 0.0183
-6.000 -0.4814 0.01247 0.00611 -0.0379 0.9740 0.0195
-5.750 -0.4485 0.01202 0.00561 -0.0392 0.9713 0.0206
-5.500 -0.4194 0.01165 0.00521 -0.0395 0.9665 0.0219
-5.250 -0.3892 0.01128 0.00479 -0.0401 0.9617 0.0230
-5.000 -0.3563 0.01092 0.00438 -0.0412 0.9581 0.0239
-4.750 -0.3268 0.01053 0.00394 -0.0416 0.9522 0.0256
-4.500 -0.2955 0.01018 0.00360 -0.0423 0.9464 0.0284
-4.250 -0.2626 0.00988 0.00329 -0.0434 0.9410 0.0328
-4.000 -0.2318 0.00956 0.00300 -0.0440 0.9329 0.0430
-3.750 -0.1998 0.00925 0.00274 -0.0450 0.9248 0.0586
-3.500 -0.1684 0.00898 0.00251 -0.0457 0.9151 0.0756
-3.250 -0.1390 0.00875 0.00231 -0.0460 0.9037 0.0936
-3.000 -0.1102 0.00851 0.00212 -0.0462 0.8912 0.1178
-2.750 -0.0826 0.00824 0.00196 -0.0462 0.8776 0.1537
-2.500 -0.0560 0.00795 0.00181 -0.0459 0.8630 0.2051
-2.250 -0.0301 0.00766 0.00168 -0.0456 0.8472 0.2630
-2.000 -0.0045 0.00739 0.00156 -0.0452 0.8308 0.3261
-1.750 0.0210 0.00718 0.00147 -0.0447 0.8139 0.3814
-1.500 0.0464 0.00698 0.00138 -0.0442 0.7968 0.4375
-1.250 0.0707 0.00669 0.00131 -0.0435 0.7793 0.5202
-1.000 0.0941 0.00637 0.00126 -0.0425 0.7613 0.6152
-0.750 0.1170 0.00612 0.00127 -0.0413 0.7427 0.7060
-0.500 0.1411 0.00608 0.00132 -0.0402 0.7233 0.7656
-0.250 0.1662 0.00612 0.00134 -0.0394 0.7005 0.7967
0.000 0.1912 0.00620 0.00136 -0.0386 0.6753 0.8187
0.250 0.2161 0.00630 0.00139 -0.0377 0.6505 0.8375
0.500 0.2415 0.00639 0.00142 -0.0370 0.6279 0.8523
1.000 0.2923 0.00658 0.00150 -0.0356 0.5861 0.8762
1.250 0.3170 0.00671 0.00155 -0.0348 0.5624 0.8884
1.500 0.3420 0.00683 0.00160 -0.0341 0.5383 0.8995
1.750 0.3671 0.00695 0.00166 -0.0333 0.5181 0.9095
2.000 0.3921 0.00707 0.00174 -0.0326 0.4965 0.9201
2.250 0.4169 0.00722 0.00182 -0.0318 0.4721 0.9316
2.500 0.4425 0.00738 0.00190 -0.0312 0.4478 0.9431
2.750 0.4699 0.00758 0.00201 -0.0311 0.4187 0.9533
3.000 0.4990 0.00784 0.00213 -0.0314 0.3833 0.9616
3.250 0.5280 0.00810 0.00226 -0.0318 0.3497 0.9694
3.500 0.5592 0.00837 0.00241 -0.0327 0.3179 0.9742
3.750 0.5900 0.00863 0.00256 -0.0335 0.2904 0.9795
4.000 0.6203 0.00895 0.00274 -0.0343 0.2562 0.9848
4.250 0.6515 0.00930 0.00295 -0.0353 0.2206 0.9895
5.000 0.7331 0.01036 0.00367 -0.0357 0.1459 1.0000
5.250 0.7549 0.01063 0.00391 -0.0347 0.1332 1.0000
5.500 0.7775 0.01091 0.00416 -0.0337 0.1200 1.0000
5.750 0.8005 0.01122 0.00441 -0.0329 0.1061 1.0000
6.000 0.8237 0.01154 0.00468 -0.0321 0.0934 1.0000
6.250 0.8470 0.01188 0.00497 -0.0314 0.0822 1.0000
6.500 0.8705 0.01221 0.00530 -0.0307 0.0736 1.0000
6.750 0.8938 0.01258 0.00565 -0.0300 0.0657 1.0000
7.000 0.9176 0.01290 0.00599 -0.0293 0.0604 1.0000
7.250 0.9407 0.01330 0.00637 -0.0286 0.0540 1.0000
7.500 0.9643 0.01365 0.00675 -0.0280 0.0493 1.0000
7.750 0.9867 0.01411 0.00719 -0.0272 0.0424 1.0000
8.000 1.0099 0.01447 0.00759 -0.0265 0.0381 1.0000
8.250 1.0320 0.01496 0.00805 -0.0257 0.0331 1.0000
8.500 1.0547 0.01536 0.00850 -0.0249 0.0303 1.0000
8.750 1.0767 0.01582 0.00898 -0.0241 0.0272 1.0000
9.000 1.0980 0.01635 0.00954 -0.0232 0.0243 1.0000
9.250 1.1198 0.01680 0.01005 -0.0224 0.0221 1.0000
9.500 1.1403 0.01737 0.01063 -0.0214 0.0194 1.0000
9.750 1.1609 0.01791 0.01122 -0.0204 0.0171 1.0000
10.000 1.1805 0.01851 0.01186 -0.0193 0.0147 1.0000
10.250 1.1995 0.01915 0.01255 -0.0181 0.0129 1.0000
10.500 1.2177 0.01982 0.01329 -0.0169 0.0111 1.0000
10.750 1.2341 0.02061 0.01413 -0.0154 0.0099 1.0000
11.000 1.2506 0.02133 0.01495 -0.0139 0.0091 1.0000
11.250 1.2657 0.02210 0.01580 -0.0122 0.0084 1.0000
11.500 1.2780 0.02291 0.01667 -0.0101 0.0077 1.0000
11.750 1.2877 0.02384 0.01768 -0.0077 0.0072 1.0000
12.000 1.2952 0.02491 0.01886 -0.0051 0.0067 1.0000
12.250 1.3049 0.02584 0.01990 -0.0030 0.0064 1.0000
12.500 1.3124 0.02694 0.02113 -0.0008 0.0062 1.0000
12.750 1.3183 0.02817 0.02248 0.0014 0.0060 1.0000
13.000 1.3231 0.02953 0.02396 0.0034 0.0058 1.0000
13.250 1.3264 0.03107 0.02562 0.0052 0.0057 1.0000
13.500 1.3290 0.03275 0.02743 0.0068 0.0055 1.0000
13.750 1.3295 0.03474 0.02955 0.0081 0.0054 1.0000
14.000 1.3293 0.03693 0.03186 0.0091 0.0052 1.0000
14.250 1.3264 0.03955 0.03462 0.0097 0.0051 1.0000
14.500 1.3205 0.04273 0.03794 0.0097 0.0050 1.0000
14.750 1.3143 0.04623 0.04158 0.0092 0.0050 1.0000
15.000 1.3057 0.05031 0.04581 0.0081 0.0049 1.0000
15.250 1.2964 0.05481 0.05046 0.0064 0.0049 1.0000
15.500 1.2796 0.06078 0.05659 0.0036 0.0047 1.0000
15.750 1.2672 0.06646 0.06243 0.0008 0.0048 1.0000
16.000 1.2462 0.07393 0.07007 -0.0033 0.0047 1.0000
16.250 1.2281 0.08132 0.07761 -0.0074 0.0047 1.0000
16.500 1.2081 0.08935 0.08581 -0.0119 0.0048 1.0000
16.750 1.1845 0.09846 0.09507 -0.0171 0.0048 1.0000
17.000 1.1624 0.10754 0.10430 -0.0222 0.0048 1.0000
17.250 1.1394 0.11704 0.11394 -0.0275 0.0049 1.0000
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