RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 100,000 Max Cl/Cd: 47.58 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14-il-100000-n5.txt Download as CSV file: xf-rg14-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5006 0.11540 0.11014 -0.0125 1.0000 0.0299
-10.250 -0.4986 0.11122 0.10599 -0.0137 1.0000 0.0279
-10.000 -0.4999 0.10630 0.10112 -0.0159 1.0000 0.0259
-9.500 -0.5048 0.09532 0.09024 -0.0220 1.0000 0.0223
-9.250 -0.5055 0.09120 0.08616 -0.0235 1.0000 0.0219
-9.000 -0.5074 0.08688 0.08191 -0.0253 1.0000 0.0216
-8.750 -0.5111 0.08232 0.07740 -0.0275 1.0000 0.0213
-8.500 -0.5164 0.07764 0.07280 -0.0301 1.0000 0.0211
-8.250 -0.5255 0.07281 0.06803 -0.0334 1.0000 0.0208
-8.000 -0.5342 0.06777 0.06299 -0.0358 1.0000 0.0205
-7.750 -0.5407 0.06274 0.05791 -0.0373 1.0000 0.0202
-7.500 -0.5453 0.05791 0.05296 -0.0379 1.0000 0.0199
-7.250 -0.5481 0.05309 0.04796 -0.0379 1.0000 0.0197
-7.000 -0.5479 0.04845 0.04307 -0.0372 1.0000 0.0194
-6.750 -0.5447 0.04400 0.03828 -0.0362 1.0000 0.0193
-6.500 -0.5383 0.03983 0.03371 -0.0348 1.0000 0.0192
-6.250 -0.5287 0.03599 0.02940 -0.0331 1.0000 0.0192
-6.000 -0.5158 0.03265 0.02558 -0.0315 1.0000 0.0194
-5.750 -0.5001 0.02970 0.02213 -0.0298 1.0000 0.0199
-5.500 -0.4816 0.02756 0.01948 -0.0283 1.0000 0.0215
-5.250 -0.4621 0.02565 0.01715 -0.0268 1.0000 0.0232
-5.000 -0.4429 0.02375 0.01508 -0.0256 1.0000 0.0249
-4.750 -0.4222 0.02220 0.01334 -0.0243 1.0000 0.0263
-4.500 -0.4012 0.02085 0.01183 -0.0230 1.0000 0.0280
-4.250 -0.3802 0.01965 0.01048 -0.0216 1.0000 0.0303
-4.000 -0.3595 0.01855 0.00922 -0.0202 1.0000 0.0338
-3.750 -0.3387 0.01774 0.00838 -0.0191 1.0000 0.0439
-3.500 -0.3179 0.01690 0.00753 -0.0180 1.0000 0.0605
-3.250 -0.2968 0.01619 0.00693 -0.0170 1.0000 0.0874
-3.000 -0.2755 0.01555 0.00644 -0.0161 1.0000 0.1264
-2.750 -0.2470 0.01484 0.00607 -0.0169 0.9968 0.2001
-2.500 -0.2129 0.01407 0.00581 -0.0188 0.9903 0.3261
-2.250 -0.1810 0.01313 0.00569 -0.0200 0.9837 0.5222
-2.000 -0.1564 0.01254 0.00590 -0.0181 0.9760 0.7468
-1.750 -0.1224 0.01257 0.00599 -0.0182 0.9692 0.8590
-1.500 -0.0810 0.01260 0.00595 -0.0201 0.9626 0.9205
-1.250 -0.0233 0.01265 0.00583 -0.0257 0.9598 0.9618
-1.000 0.0396 0.01263 0.00560 -0.0328 0.9577 0.9885
-0.750 0.0876 0.01257 0.00539 -0.0371 0.9501 1.0000
-0.500 0.1271 0.01249 0.00519 -0.0397 0.9397 1.0000
-0.250 0.1668 0.01239 0.00500 -0.0422 0.9289 1.0000
0.000 0.2027 0.01228 0.00483 -0.0439 0.9154 1.0000
0.250 0.2371 0.01217 0.00467 -0.0452 0.9002 1.0000
0.500 0.2699 0.01208 0.00453 -0.0461 0.8831 1.0000
0.750 0.3027 0.01200 0.00440 -0.0470 0.8653 1.0000
1.000 0.3353 0.01192 0.00428 -0.0477 0.8470 1.0000
1.250 0.3635 0.01190 0.00424 -0.0476 0.8256 1.0000
1.500 0.3923 0.01188 0.00417 -0.0475 0.8042 1.0000
1.750 0.4182 0.01191 0.00415 -0.0468 0.7806 1.0000
2.000 0.4435 0.01197 0.00416 -0.0460 0.7561 1.0000
2.250 0.4683 0.01206 0.00423 -0.0451 0.7308 1.0000
2.500 0.4923 0.01218 0.00428 -0.0441 0.7046 1.0000
2.750 0.5158 0.01233 0.00437 -0.0430 0.6772 1.0000
3.000 0.5390 0.01251 0.00448 -0.0418 0.6489 1.0000
3.250 0.5618 0.01271 0.00462 -0.0406 0.6195 1.0000
3.500 0.5845 0.01295 0.00484 -0.0393 0.5890 1.0000
3.750 0.6070 0.01322 0.00503 -0.0381 0.5575 1.0000
4.000 0.6293 0.01351 0.00526 -0.0369 0.5248 1.0000
4.250 0.6514 0.01384 0.00552 -0.0357 0.4909 1.0000
4.500 0.6733 0.01421 0.00581 -0.0345 0.4559 1.0000
4.750 0.6950 0.01462 0.00613 -0.0332 0.4199 1.0000
5.000 0.7165 0.01506 0.00655 -0.0321 0.3824 1.0000
5.250 0.7378 0.01555 0.00696 -0.0309 0.3442 1.0000
5.500 0.7588 0.01610 0.00742 -0.0298 0.3056 1.0000
5.750 0.7795 0.01671 0.00793 -0.0286 0.2670 1.0000
6.000 0.8000 0.01738 0.00851 -0.0275 0.2279 1.0000
6.250 0.8203 0.01811 0.00915 -0.0265 0.1909 1.0000
6.500 0.8401 0.01894 0.00994 -0.0253 0.1575 1.0000
6.750 0.8598 0.01982 0.01075 -0.0242 0.1263 1.0000
7.000 0.8789 0.02080 0.01166 -0.0231 0.1001 1.0000
7.250 0.8971 0.02188 0.01267 -0.0219 0.0779 1.0000
7.500 0.9152 0.02302 0.01384 -0.0205 0.0605 1.0000
7.750 0.9316 0.02435 0.01523 -0.0189 0.0488 1.0000
8.000 0.9480 0.02568 0.01660 -0.0175 0.0385 1.0000
8.250 0.9609 0.02739 0.01836 -0.0156 0.0327 1.0000
8.500 0.9777 0.02877 0.01997 -0.0141 0.0274 1.0000
8.750 0.9917 0.03028 0.02164 -0.0126 0.0232 1.0000
9.000 1.0031 0.03259 0.02411 -0.0106 0.0213 1.0000
9.250 1.0173 0.03480 0.02662 -0.0089 0.0198 1.0000
9.500 1.0302 0.03720 0.02931 -0.0073 0.0188 1.0000
9.750 1.0403 0.03942 0.03181 -0.0055 0.0173 1.0000
10.000 1.0479 0.04147 0.03407 -0.0038 0.0162 1.0000
10.250 1.0511 0.04356 0.03631 -0.0018 0.0152 1.0000
10.750 1.0420 0.04943 0.04268 0.0030 0.0142 1.0000
11.000 1.0335 0.05255 0.04614 0.0048 0.0138 1.0000
11.250 1.0223 0.05614 0.05001 0.0057 0.0138 1.0000
11.500 1.0082 0.06029 0.05443 0.0056 0.0137 1.0000
11.750 0.9931 0.06497 0.05934 0.0043 0.0137 1.0000
12.000 0.9769 0.07037 0.06495 0.0018 0.0138 1.0000
12.250 0.9595 0.07664 0.07141 -0.0019 0.0139 1.0000
12.500 0.9406 0.08402 0.07896 -0.0069 0.0139 1.0000
12.750 0.9215 0.09232 0.08739 -0.0126 0.0141 1.0000
13.000 0.9032 0.10113 0.09628 -0.0184 0.0143 1.0000
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Polar data table (+)
Polar graphs
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