RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 500,000 Max Cl/Cd: 83.5 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14-il-500000.txt Download as CSV file: xf-rg14-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5073 0.08436 0.08214 -0.0241 1.0000 0.0167
-8.750 -0.5100 0.08025 0.07807 -0.0260 1.0000 0.0169
-8.500 -0.5152 0.07594 0.07379 -0.0283 1.0000 0.0170
-8.250 -0.5264 0.07139 0.06929 -0.0315 1.0000 0.0172
-5.500 -0.5006 0.02134 0.01641 -0.0243 0.9984 0.0155
-5.250 -0.4684 0.01854 0.01330 -0.0254 0.9962 0.0140
-5.000 -0.4355 0.01601 0.01040 -0.0265 0.9944 0.0134
-4.750 -0.4034 0.01427 0.00843 -0.0273 0.9917 0.0135
-4.500 -0.3701 0.01302 0.00703 -0.0284 0.9886 0.0136
-4.250 -0.3349 0.01214 0.00603 -0.0299 0.9858 0.0144
-4.000 -0.2992 0.01103 0.00479 -0.0316 0.9834 0.0167
-3.750 -0.2655 0.01047 0.00417 -0.0329 0.9794 0.0200
-3.500 -0.2315 0.00977 0.00352 -0.0341 0.9749 0.0411
-3.250 -0.1946 0.00927 0.00318 -0.0362 0.9717 0.0799
-3.000 -0.1564 0.00880 0.00292 -0.0387 0.9694 0.1323
-2.750 -0.1265 0.00830 0.00269 -0.0393 0.9626 0.2020
-2.250 -0.0580 0.00687 0.00224 -0.0428 0.9546 0.4756
-2.000 -0.0305 0.00619 0.00208 -0.0428 0.9465 0.6210
-1.750 -0.0028 0.00569 0.00206 -0.0424 0.9388 0.7605
-1.500 0.0273 0.00554 0.00202 -0.0424 0.9300 0.8212
-1.250 0.0555 0.00546 0.00195 -0.0420 0.9181 0.8510
-1.000 0.0837 0.00543 0.00189 -0.0416 0.9052 0.8727
-0.750 0.1102 0.00540 0.00185 -0.0408 0.8908 0.8912
-0.500 0.1360 0.00541 0.00180 -0.0398 0.8751 0.9072
-0.250 0.1611 0.00543 0.00177 -0.0388 0.8581 0.9209
0.000 0.1860 0.00547 0.00175 -0.0377 0.8396 0.9338
0.250 0.2121 0.00552 0.00173 -0.0369 0.8207 0.9461
0.500 0.2396 0.00559 0.00172 -0.0365 0.8009 0.9568
0.750 0.2717 0.00568 0.00172 -0.0371 0.7799 0.9646
1.000 0.3056 0.00578 0.00173 -0.0382 0.7574 0.9720
1.250 0.3437 0.00591 0.00175 -0.0403 0.7333 0.9774
1.500 0.3795 0.00604 0.00177 -0.0419 0.7071 0.9830
1.750 0.4196 0.00616 0.00178 -0.0446 0.6795 0.9868
2.000 0.4570 0.00630 0.00181 -0.0467 0.6495 0.9918
2.250 0.4936 0.00644 0.00185 -0.0487 0.6182 0.9960
2.500 0.5298 0.00660 0.00188 -0.0507 0.5855 0.9999
2.750 0.5499 0.00674 0.00192 -0.0492 0.5568 1.0000
3.000 0.5692 0.00690 0.00198 -0.0476 0.5285 1.0000
3.250 0.5882 0.00708 0.00206 -0.0459 0.4980 1.0000
3.500 0.6074 0.00728 0.00218 -0.0443 0.4678 1.0000
3.750 0.6271 0.00751 0.00231 -0.0427 0.4372 1.0000
4.000 0.6475 0.00777 0.00245 -0.0414 0.4057 1.0000
4.250 0.6688 0.00805 0.00262 -0.0401 0.3725 1.0000
4.500 0.6905 0.00837 0.00281 -0.0390 0.3377 1.0000
4.750 0.7132 0.00869 0.00305 -0.0381 0.3054 1.0000
5.000 0.7358 0.00908 0.00330 -0.0373 0.2688 1.0000
5.250 0.7585 0.00949 0.00357 -0.0364 0.2306 1.0000
5.500 0.7810 0.00997 0.00388 -0.0356 0.1904 1.0000
5.750 0.8039 0.01045 0.00422 -0.0349 0.1576 1.0000
6.000 0.8270 0.01092 0.00458 -0.0342 0.1291 1.0000
6.250 0.8499 0.01143 0.00501 -0.0335 0.1029 1.0000
6.500 0.8724 0.01199 0.00544 -0.0327 0.0758 1.0000
6.750 0.8946 0.01259 0.00592 -0.0319 0.0537 1.0000
7.000 0.9169 0.01319 0.00643 -0.0312 0.0367 1.0000
7.250 0.9383 0.01393 0.00712 -0.0302 0.0235 1.0000
7.500 0.9570 0.01505 0.00828 -0.0286 0.0144 1.0000
7.750 0.9789 0.01571 0.00902 -0.0276 0.0117 1.0000
8.000 0.9965 0.01688 0.01029 -0.0260 0.0100 1.0000
8.250 1.0119 0.01832 0.01192 -0.0240 0.0093 1.0000
8.500 1.0299 0.01943 0.01316 -0.0225 0.0090 1.0000
8.750 1.0467 0.02073 0.01462 -0.0209 0.0087 1.0000
9.000 1.0628 0.02219 0.01624 -0.0191 0.0085 1.0000
9.250 1.0794 0.02356 0.01777 -0.0176 0.0081 1.0000
9.500 1.0971 0.02454 0.01886 -0.0164 0.0075 1.0000
9.750 1.1110 0.02623 0.02073 -0.0146 0.0072 1.0000
10.000 1.1239 0.02788 0.02257 -0.0128 0.0070 1.0000
10.250 1.1337 0.02995 0.02486 -0.0106 0.0069 1.0000
10.500 1.1414 0.03191 0.02704 -0.0084 0.0068 1.0000
10.750 1.1429 0.03419 0.02959 -0.0054 0.0067 1.0000
11.000 1.1407 0.03628 0.03188 -0.0021 0.0066 1.0000
11.250 1.1334 0.03892 0.03477 0.0012 0.0066 1.0000
11.500 1.1202 0.04231 0.03844 0.0041 0.0067 1.0000
11.750 1.1118 0.04495 0.04124 0.0056 0.0065 1.0000
12.000 1.0989 0.04848 0.04498 0.0064 0.0065 1.0000
12.250 1.0846 0.05259 0.04928 0.0060 0.0065 1.0000
12.500 1.0648 0.05813 0.05504 0.0042 0.0065 1.0000
12.750 1.0418 0.06504 0.06218 0.0007 0.0066 1.0000
13.000 1.0131 0.07414 0.07152 -0.0051 0.0068 1.0000
13.250 0.9974 0.08157 0.07907 -0.0103 0.0067 1.0000
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Polar data table (+)
Polar graphs
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