RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 500,000 Max Cl/Cd: 71.88 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1410-il-500000-n5.txt Download as CSV file: xf-rg1410-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7935 0.08664 0.08404 -0.0305 1.0000 0.0083
-13.750 -0.8697 0.06704 0.06430 -0.0423 1.0000 0.0080
-13.500 -0.9215 0.05039 0.04737 -0.0560 1.0000 0.0077
-13.250 -0.9457 0.04311 0.03987 -0.0618 1.0000 0.0076
-13.000 -0.9622 0.03892 0.03548 -0.0629 1.0000 0.0078
-12.750 -0.9762 0.03589 0.03225 -0.0618 1.0000 0.0078
-12.500 -0.9875 0.03367 0.02986 -0.0591 1.0000 0.0079
-12.250 -0.9954 0.03201 0.02803 -0.0553 1.0000 0.0080
-12.000 -0.9948 0.03033 0.02616 -0.0526 1.0000 0.0082
-11.750 -0.9906 0.02878 0.02440 -0.0501 1.0000 0.0084
-11.500 -0.9843 0.02738 0.02287 -0.0477 1.0000 0.0087
-11.250 -0.9717 0.02653 0.02196 -0.0459 1.0000 0.0090
-11.000 -0.9586 0.02565 0.02098 -0.0441 1.0000 0.0092
-10.750 -0.9440 0.02487 0.02011 -0.0424 1.0000 0.0095
-10.500 -0.9291 0.02408 0.01921 -0.0407 1.0000 0.0098
-10.250 -0.9149 0.02312 0.01812 -0.0388 1.0000 0.0102
-10.000 -0.9000 0.02220 0.01706 -0.0370 1.0000 0.0106
-9.750 -0.8843 0.02133 0.01604 -0.0352 1.0000 0.0111
-9.500 -0.8680 0.02051 0.01507 -0.0335 1.0000 0.0114
-9.250 -0.8513 0.01973 0.01416 -0.0317 1.0000 0.0117
-9.000 -0.8356 0.01884 0.01320 -0.0299 1.0000 0.0122
-8.750 -0.8091 0.01829 0.01258 -0.0302 0.9989 0.0128
-8.500 -0.7780 0.01780 0.01204 -0.0313 0.9969 0.0136
-8.250 -0.7470 0.01718 0.01132 -0.0324 0.9950 0.0144
-8.000 -0.7168 0.01655 0.01057 -0.0333 0.9929 0.0151
-7.750 -0.6872 0.01597 0.00987 -0.0339 0.9902 0.0155
-7.500 -0.6579 0.01512 0.00895 -0.0347 0.9874 0.0164
-7.250 -0.6263 0.01456 0.00836 -0.0359 0.9850 0.0174
-7.000 -0.5933 0.01411 0.00786 -0.0372 0.9832 0.0183
-6.750 -0.5661 0.01362 0.00731 -0.0373 0.9785 0.0191
-6.500 -0.5352 0.01316 0.00678 -0.0381 0.9748 0.0200
-6.250 -0.5024 0.01274 0.00630 -0.0393 0.9720 0.0208
-6.000 -0.4729 0.01214 0.00567 -0.0398 0.9679 0.0221
-5.750 -0.4441 0.01173 0.00523 -0.0401 0.9625 0.0232
-5.500 -0.4118 0.01135 0.00481 -0.0411 0.9590 0.0246
-5.250 -0.3802 0.01102 0.00444 -0.0420 0.9547 0.0262
-5.000 -0.3511 0.01067 0.00407 -0.0423 0.9482 0.0288
-4.750 -0.3180 0.01033 0.00374 -0.0434 0.9437 0.0326
-4.500 -0.2878 0.01001 0.00343 -0.0439 0.9366 0.0394
-4.250 -0.2551 0.00970 0.00315 -0.0450 0.9298 0.0508
-4.000 -0.2246 0.00942 0.00291 -0.0455 0.9206 0.0636
-3.750 -0.1934 0.00916 0.00267 -0.0462 0.9111 0.0793
-3.500 -0.1642 0.00891 0.00247 -0.0465 0.8999 0.0980
-3.250 -0.1362 0.00869 0.00229 -0.0465 0.8875 0.1198
-3.000 -0.1088 0.00846 0.00212 -0.0464 0.8745 0.1464
-2.750 -0.0823 0.00819 0.00197 -0.0462 0.8609 0.1884
-2.500 -0.0563 0.00793 0.00183 -0.0458 0.8464 0.2370
-2.250 -0.0304 0.00770 0.00171 -0.0454 0.8310 0.2830
-2.000 -0.0048 0.00750 0.00160 -0.0449 0.8149 0.3314
-1.750 0.0205 0.00728 0.00151 -0.0444 0.7983 0.3865
-1.500 0.0456 0.00707 0.00143 -0.0438 0.7815 0.4441
-1.250 0.0698 0.00681 0.00136 -0.0431 0.7644 0.5208
-1.000 0.0935 0.00654 0.00131 -0.0422 0.7468 0.6012
-0.750 0.1167 0.00630 0.00131 -0.0411 0.7285 0.6824
-0.500 0.1402 0.00623 0.00136 -0.0399 0.7076 0.7483
-0.250 0.1650 0.00627 0.00139 -0.0390 0.6844 0.7839
0.000 0.1902 0.00635 0.00141 -0.0383 0.6619 0.8074
0.250 0.2156 0.00642 0.00145 -0.0375 0.6419 0.8265
0.500 0.2408 0.00652 0.00148 -0.0368 0.6186 0.8415
0.750 0.2662 0.00663 0.00152 -0.0361 0.5950 0.8540
1.000 0.2914 0.00675 0.00156 -0.0354 0.5733 0.8657
1.250 0.3167 0.00685 0.00162 -0.0346 0.5536 0.8773
1.500 0.3420 0.00695 0.00168 -0.0340 0.5346 0.8877
2.000 0.3922 0.00721 0.00181 -0.0325 0.4910 0.9067
2.250 0.4166 0.00736 0.00189 -0.0317 0.4671 0.9172
2.500 0.4414 0.00750 0.00197 -0.0309 0.4447 0.9280
2.750 0.4668 0.00767 0.00208 -0.0303 0.4234 0.9380
3.000 0.4930 0.00789 0.00219 -0.0299 0.3922 0.9478
3.250 0.5199 0.00814 0.00232 -0.0298 0.3596 0.9573
3.500 0.5499 0.00838 0.00246 -0.0303 0.3308 0.9637
4.000 0.6098 0.00894 0.00278 -0.0316 0.2724 0.9748
4.250 0.6400 0.00926 0.00298 -0.0323 0.2410 0.9803
4.500 0.6706 0.00959 0.00319 -0.0332 0.2116 0.9852
5.000 0.7322 0.01034 0.00370 -0.0351 0.1572 0.9955
5.250 0.7616 0.01065 0.00396 -0.0357 0.1433 1.0000
5.500 0.7819 0.01093 0.00419 -0.0343 0.1326 1.0000
5.750 0.8036 0.01119 0.00443 -0.0332 0.1212 1.0000
6.000 0.8259 0.01149 0.00467 -0.0323 0.1081 1.0000
6.250 0.8483 0.01182 0.00496 -0.0314 0.0949 1.0000
6.500 0.8713 0.01214 0.00525 -0.0305 0.0852 1.0000
6.750 0.8944 0.01247 0.00556 -0.0298 0.0776 1.0000
7.000 0.9173 0.01283 0.00590 -0.0290 0.0705 1.0000
7.250 0.9405 0.01317 0.00626 -0.0282 0.0645 1.0000
7.500 0.9633 0.01355 0.00663 -0.0275 0.0585 1.0000
7.750 0.9863 0.01391 0.00702 -0.0267 0.0538 1.0000
8.000 1.0088 0.01431 0.00742 -0.0259 0.0486 1.0000
8.250 1.0311 0.01473 0.00785 -0.0251 0.0440 1.0000
8.500 1.0532 0.01516 0.00828 -0.0243 0.0388 1.0000
8.750 1.0748 0.01562 0.00875 -0.0234 0.0347 1.0000
9.000 1.0966 0.01605 0.00922 -0.0225 0.0319 1.0000
9.250 1.1172 0.01658 0.00974 -0.0215 0.0283 1.0000
9.500 1.1382 0.01705 0.01027 -0.0205 0.0263 1.0000
9.750 1.1586 0.01755 0.01082 -0.0195 0.0241 1.0000
10.000 1.1776 0.01815 0.01144 -0.0183 0.0215 1.0000
10.250 1.1973 0.01867 0.01202 -0.0172 0.0199 1.0000
10.500 1.2156 0.01927 0.01265 -0.0159 0.0175 1.0000
10.750 1.2329 0.01991 0.01334 -0.0145 0.0157 1.0000
11.000 1.2497 0.02055 0.01404 -0.0130 0.0140 1.0000
11.250 1.2630 0.02129 0.01483 -0.0110 0.0123 1.0000
11.500 1.2761 0.02198 0.01560 -0.0090 0.0114 1.0000
11.750 1.2877 0.02276 0.01645 -0.0068 0.0103 1.0000
12.000 1.2981 0.02363 0.01739 -0.0046 0.0095 1.0000
12.250 1.3067 0.02464 0.01847 -0.0023 0.0089 1.0000
12.500 1.3160 0.02560 0.01953 -0.0002 0.0084 1.0000
12.750 1.3245 0.02663 0.02066 0.0017 0.0079 1.0000
13.000 1.3310 0.02784 0.02197 0.0037 0.0076 1.0000
13.250 1.3364 0.02918 0.02342 0.0055 0.0071 1.0000
13.500 1.3401 0.03072 0.02506 0.0072 0.0068 1.0000
13.750 1.3404 0.03263 0.02708 0.0089 0.0065 1.0000
14.000 1.3397 0.03475 0.02932 0.0101 0.0063 1.0000
14.250 1.3400 0.03692 0.03162 0.0110 0.0062 1.0000
14.500 1.3387 0.03942 0.03425 0.0115 0.0061 1.0000
14.750 1.3372 0.04211 0.03708 0.0116 0.0059 1.0000
15.000 1.3327 0.04533 0.04044 0.0113 0.0059 1.0000
15.250 1.3266 0.04899 0.04424 0.0105 0.0057 1.0000
15.500 1.3180 0.05323 0.04864 0.0092 0.0057 1.0000
15.750 1.3081 0.05792 0.05348 0.0073 0.0057 1.0000
16.000 1.2972 0.06306 0.05877 0.0050 0.0055 1.0000
16.250 1.2818 0.06920 0.06507 0.0019 0.0056 1.0000
16.500 1.2662 0.07570 0.07172 -0.0015 0.0055 1.0000
16.750 1.2469 0.08317 0.07935 -0.0055 0.0055 1.0000
17.000 1.2258 0.09127 0.08761 -0.0100 0.0055 1.0000
17.250 1.2024 0.10016 0.09665 -0.0150 0.0056 1.0000
17.500 1.1777 0.10955 0.10620 -0.0203 0.0056 1.0000
17.750 1.1532 0.11923 0.11602 -0.0257 0.0057 1.0000
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