RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 200,000 Max Cl/Cd: 57.7 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg149-il-200000-n5.txt Download as CSV file: xf-rg149-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9% 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 -0.5585 0.08282 0.07920 -0.0275 1.0000 0.0151
-9.750 -0.5679 0.07691 0.07334 -0.0308 1.0000 0.0149
-9.500 -0.5850 0.06879 0.06529 -0.0364 1.0000 0.0148
-9.250 -0.6122 0.05894 0.05540 -0.0439 1.0000 0.0145
-9.000 -0.6400 0.05247 0.04877 -0.0442 1.0000 0.0144
-8.750 -0.6595 0.04669 0.04271 -0.0433 1.0000 0.0143
-8.500 -0.6749 0.04081 0.03638 -0.0413 1.0000 0.0144
-8.250 -0.6802 0.03603 0.03109 -0.0389 1.0000 0.0147
-8.000 -0.6780 0.03211 0.02657 -0.0365 1.0000 0.0151
-7.750 -0.6696 0.02914 0.02313 -0.0343 1.0000 0.0155
-7.500 -0.6562 0.02739 0.02124 -0.0327 1.0000 0.0164
-7.250 -0.6393 0.02639 0.02013 -0.0313 1.0000 0.0173
-7.000 -0.6222 0.02522 0.01875 -0.0299 1.0000 0.0186
-6.750 -0.6051 0.02355 0.01676 -0.0282 1.0000 0.0197
-6.500 -0.5868 0.02206 0.01497 -0.0266 1.0000 0.0206
-6.250 -0.5673 0.02095 0.01360 -0.0252 1.0000 0.0214
-6.000 -0.5490 0.01951 0.01207 -0.0238 1.0000 0.0230
-5.750 -0.5291 0.01885 0.01135 -0.0226 1.0000 0.0247
-5.500 -0.5062 0.01798 0.01036 -0.0219 0.9994 0.0261
-5.250 -0.4729 0.01704 0.00928 -0.0232 0.9960 0.0275
-5.000 -0.4395 0.01632 0.00844 -0.0245 0.9924 0.0296
-4.750 -0.4075 0.01541 0.00749 -0.0258 0.9881 0.0321
-4.500 -0.3730 0.01480 0.00681 -0.0273 0.9842 0.0345
-4.250 -0.3410 0.01426 0.00619 -0.0284 0.9790 0.0372
-4.000 -0.3079 0.01370 0.00560 -0.0296 0.9738 0.0422
-3.750 -0.2727 0.01323 0.00514 -0.0313 0.9697 0.0529
-3.500 -0.2428 0.01273 0.00469 -0.0318 0.9625 0.0727
-3.250 -0.2079 0.01228 0.00435 -0.0335 0.9578 0.1040
-3.000 -0.1772 0.01185 0.00407 -0.0342 0.9505 0.1419
-2.750 -0.1441 0.01124 0.00380 -0.0357 0.9448 0.2223
-2.500 -0.1144 0.01055 0.00359 -0.0365 0.9371 0.3354
-2.250 -0.0824 0.00999 0.00338 -0.0375 0.9301 0.4333
-2.000 -0.0547 0.00942 0.00323 -0.0375 0.9206 0.5433
-1.750 -0.0268 0.00886 0.00321 -0.0371 0.9126 0.6812
-1.500 0.0001 0.00867 0.00329 -0.0360 0.9021 0.7810
-1.250 0.0289 0.00861 0.00326 -0.0356 0.8908 0.8270
-1.000 0.0587 0.00857 0.00320 -0.0354 0.8789 0.8564
-0.750 0.0889 0.00854 0.00314 -0.0352 0.8660 0.8793
-0.500 0.1188 0.00854 0.00308 -0.0351 0.8517 0.8999
-0.250 0.1505 0.00854 0.00302 -0.0353 0.8365 0.9160
0.000 0.1831 0.00856 0.00297 -0.0359 0.8202 0.9300
0.250 0.2172 0.00859 0.00293 -0.0367 0.8029 0.9431
0.500 0.2535 0.00864 0.00289 -0.0381 0.7844 0.9538
0.750 0.2906 0.00869 0.00286 -0.0398 0.7636 0.9623
1.000 0.3259 0.00877 0.00283 -0.0412 0.7397 0.9712
1.250 0.3644 0.00886 0.00279 -0.0432 0.7110 0.9775
1.500 0.3991 0.00896 0.00276 -0.0446 0.6819 0.9843
1.750 0.4344 0.00907 0.00276 -0.0462 0.6533 0.9898
2.000 0.4674 0.00920 0.00277 -0.0473 0.6245 0.9954
2.250 0.4983 0.00935 0.00279 -0.0480 0.5914 1.0000
2.500 0.5180 0.00951 0.00287 -0.0464 0.5655 1.0000
2.750 0.5380 0.00968 0.00296 -0.0449 0.5415 1.0000
3.000 0.5575 0.00988 0.00306 -0.0433 0.5138 1.0000
3.500 0.5961 0.01040 0.00333 -0.0400 0.4475 1.0000
3.750 0.6157 0.01069 0.00350 -0.0384 0.4141 1.0000
4.000 0.6356 0.01102 0.00369 -0.0369 0.3793 1.0000
4.250 0.6561 0.01137 0.00391 -0.0356 0.3435 1.0000
4.500 0.6768 0.01176 0.00419 -0.0343 0.3084 1.0000
4.750 0.6980 0.01217 0.00447 -0.0332 0.2715 1.0000
5.000 0.7189 0.01266 0.00480 -0.0321 0.2319 1.0000
5.250 0.7400 0.01318 0.00516 -0.0310 0.1960 1.0000
5.500 0.7615 0.01371 0.00556 -0.0301 0.1677 1.0000
5.750 0.7834 0.01422 0.00602 -0.0292 0.1472 1.0000
6.000 0.8056 0.01471 0.00647 -0.0283 0.1301 1.0000
6.250 0.8279 0.01520 0.00694 -0.0275 0.1135 1.0000
6.500 0.8504 0.01569 0.00741 -0.0267 0.0989 1.0000
6.750 0.8723 0.01623 0.00792 -0.0258 0.0862 1.0000
7.000 0.8942 0.01679 0.00851 -0.0250 0.0760 1.0000
7.250 0.9161 0.01735 0.00913 -0.0241 0.0686 1.0000
7.500 0.9364 0.01807 0.00984 -0.0230 0.0618 1.0000
7.750 0.9582 0.01864 0.01052 -0.0221 0.0560 1.0000
8.000 0.9774 0.01945 0.01133 -0.0210 0.0501 1.0000
8.250 0.9990 0.02002 0.01203 -0.0201 0.0452 1.0000
8.500 1.0185 0.02077 0.01281 -0.0190 0.0396 1.0000
8.750 1.0391 0.02142 0.01357 -0.0181 0.0354 1.0000
9.000 1.0584 0.02216 0.01438 -0.0170 0.0314 1.0000
9.250 1.0759 0.02307 0.01537 -0.0157 0.0277 1.0000
9.500 1.0944 0.02386 0.01627 -0.0145 0.0243 1.0000
9.750 1.1083 0.02504 0.01750 -0.0129 0.0216 1.0000
10.000 1.1236 0.02611 0.01875 -0.0113 0.0195 1.0000
10.250 1.1379 0.02716 0.01994 -0.0097 0.0176 1.0000
10.500 1.1475 0.02849 0.02132 -0.0077 0.0159 1.0000
10.750 1.1579 0.02966 0.02269 -0.0055 0.0147 1.0000
11.000 1.1653 0.03100 0.02419 -0.0032 0.0137 1.0000
11.250 1.1712 0.03244 0.02578 -0.0009 0.0129 1.0000
11.500 1.1755 0.03400 0.02748 0.0013 0.0123 1.0000
11.750 1.1776 0.03576 0.02937 0.0033 0.0119 1.0000
12.000 1.1758 0.03795 0.03170 0.0052 0.0115 1.0000
12.250 1.1723 0.04050 0.03442 0.0067 0.0112 1.0000
12.500 1.1693 0.04321 0.03736 0.0078 0.0109 1.0000
12.750 1.1648 0.04622 0.04058 0.0083 0.0107 1.0000
13.000 1.1585 0.04966 0.04424 0.0082 0.0105 1.0000
13.250 1.1503 0.05357 0.04838 0.0075 0.0104 1.0000
13.500 1.1398 0.05813 0.05319 0.0060 0.0101 1.0000
13.750 1.1279 0.06326 0.05853 0.0037 0.0100 1.0000
14.000 1.1137 0.06918 0.06465 0.0007 0.0100 1.0000
14.250 1.0972 0.07595 0.07162 -0.0032 0.0100 1.0000
14.500 1.0789 0.08354 0.07937 -0.0079 0.0100 1.0000
14.750 1.0564 0.09249 0.08851 -0.0134 0.0101 1.0000
15.000 1.0340 0.10209 0.09827 -0.0193 0.0103 1.0000
15.250 1.0091 0.11275 0.10908 -0.0258 0.0105 1.0000
15.500 0.9808 0.12500 0.12145 -0.0329 0.0108 1.0000
15.750 0.9503 0.13851 0.13504 -0.0405 0.0111 1.0000
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