RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 200,000 Max Cl/Cd: 63.56 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1495-il-200000.txt Download as CSV file: xf-rg1495-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4131 0.08391 0.08048 -0.0276 1.0000 0.0657
-9.250 -0.4164 0.07966 0.07626 -0.0288 1.0000 0.0677
-9.000 -0.4248 0.07477 0.07141 -0.0308 1.0000 0.0696
-8.750 -0.4450 0.06858 0.06529 -0.0353 1.0000 0.0716
-8.500 -0.5749 0.06867 0.06518 -0.0410 1.0000 0.0624
-8.250 -0.5656 0.06704 0.06360 -0.0389 1.0000 0.0639
-8.000 -0.5659 0.06426 0.06080 -0.0382 1.0000 0.0659
-7.750 -0.5715 0.06061 0.05706 -0.0381 1.0000 0.0689
-7.500 -0.5946 0.05741 0.05322 -0.0372 1.0000 0.0732
-7.000 -0.6063 0.03875 0.03380 -0.0327 1.0000 0.0462
-6.750 -0.6110 0.03076 0.02462 -0.0283 1.0000 0.0388
-6.500 -0.5973 0.02812 0.02160 -0.0261 1.0000 0.0387
-6.250 -0.5824 0.02537 0.01854 -0.0243 1.0000 0.0393
-6.000 -0.5650 0.02403 0.01715 -0.0229 1.0000 0.0415
-5.750 -0.5461 0.02270 0.01565 -0.0214 1.0000 0.0433
-5.500 -0.5263 0.02113 0.01380 -0.0198 1.0000 0.0444
-5.250 -0.5058 0.01983 0.01229 -0.0184 1.0000 0.0457
-5.000 -0.4849 0.01908 0.01135 -0.0170 1.0000 0.0480
-4.750 -0.4643 0.01758 0.00977 -0.0158 1.0000 0.0507
-4.500 -0.4435 0.01672 0.00892 -0.0146 1.0000 0.0533
-4.250 -0.4226 0.01606 0.00820 -0.0133 1.0000 0.0569
-4.000 -0.4020 0.01543 0.00751 -0.0121 1.0000 0.0618
-3.750 -0.3819 0.01480 0.00695 -0.0109 1.0000 0.0693
-3.500 -0.3591 0.01414 0.00633 -0.0103 0.9994 0.0827
-3.250 -0.3198 0.01334 0.00580 -0.0131 0.9946 0.1329
-3.000 -0.2821 0.01264 0.00552 -0.0157 0.9887 0.2169
-2.750 -0.2431 0.01192 0.00543 -0.0187 0.9836 0.3521
-2.500 -0.2128 0.01094 0.00535 -0.0197 0.9760 0.5518
-2.250 -0.1808 0.01043 0.00567 -0.0197 0.9706 0.7561
-2.000 -0.1515 0.01040 0.00575 -0.0191 0.9614 0.8360
-1.750 -0.1153 0.01045 0.00581 -0.0198 0.9555 0.8845
-1.500 -0.0803 0.01051 0.00584 -0.0202 0.9476 0.9191
-1.250 -0.0286 0.01064 0.00589 -0.0241 0.9447 0.9460
-1.000 0.0339 0.01075 0.00589 -0.0304 0.9437 0.9620
-0.750 0.1007 0.01074 0.00579 -0.0379 0.9430 0.9727
-0.500 0.1613 0.01063 0.00562 -0.0443 0.9388 0.9831
-0.250 0.2240 0.01036 0.00531 -0.0512 0.9342 0.9904
0.000 0.2863 0.01002 0.00495 -0.0581 0.9292 0.9974
0.250 0.3315 0.00973 0.00463 -0.0616 0.9161 1.0000
0.500 0.3677 0.00949 0.00435 -0.0631 0.8994 1.0000
0.750 0.3950 0.00933 0.00414 -0.0628 0.8764 1.0000
1.000 0.4213 0.00920 0.00394 -0.0622 0.8532 1.0000
1.250 0.4437 0.00914 0.00380 -0.0608 0.8272 1.0000
1.500 0.4648 0.00913 0.00371 -0.0592 0.8012 1.0000
1.750 0.4861 0.00914 0.00365 -0.0577 0.7772 1.0000
2.000 0.5069 0.00918 0.00359 -0.0561 0.7515 1.0000
2.250 0.5268 0.00925 0.00356 -0.0543 0.7243 1.0000
2.500 0.5467 0.00934 0.00359 -0.0526 0.6984 1.0000
2.750 0.5666 0.00947 0.00363 -0.0509 0.6733 1.0000
3.000 0.5860 0.00961 0.00368 -0.0491 0.6468 1.0000
3.250 0.6047 0.00978 0.00375 -0.0472 0.6178 1.0000
3.500 0.6232 0.00998 0.00386 -0.0452 0.5879 1.0000
3.750 0.6416 0.01019 0.00397 -0.0433 0.5579 1.0000
4.000 0.6603 0.01043 0.00411 -0.0414 0.5278 1.0000
4.250 0.6791 0.01069 0.00428 -0.0396 0.4963 1.0000
4.500 0.6979 0.01098 0.00448 -0.0378 0.4633 1.0000
4.750 0.7167 0.01132 0.00469 -0.0360 0.4290 1.0000
5.000 0.7358 0.01168 0.00494 -0.0343 0.3905 1.0000
5.250 0.7546 0.01213 0.00522 -0.0326 0.3465 1.0000
5.500 0.7729 0.01269 0.00558 -0.0310 0.2982 1.0000
5.750 0.7912 0.01334 0.00600 -0.0294 0.2496 1.0000
6.000 0.8097 0.01405 0.00649 -0.0279 0.2103 1.0000
6.250 0.8289 0.01477 0.00704 -0.0266 0.1808 1.0000
6.500 0.8484 0.01550 0.00768 -0.0253 0.1570 1.0000
6.750 0.8668 0.01638 0.00842 -0.0239 0.1386 1.0000
7.000 0.8873 0.01707 0.00912 -0.0227 0.1228 1.0000
7.250 0.9075 0.01780 0.00982 -0.0216 0.1096 1.0000
7.500 0.9271 0.01861 0.01058 -0.0204 0.0978 1.0000
7.750 0.9482 0.01924 0.01130 -0.0193 0.0876 1.0000
8.000 0.9675 0.02020 0.01231 -0.0180 0.0792 1.0000
8.250 0.9853 0.02139 0.01343 -0.0167 0.0714 1.0000
8.500 1.0057 0.02208 0.01426 -0.0155 0.0645 1.0000
8.750 1.0234 0.02339 0.01556 -0.0143 0.0584 1.0000
9.000 1.0425 0.02412 0.01645 -0.0130 0.0527 1.0000
9.250 1.0593 0.02575 0.01807 -0.0117 0.0477 1.0000
9.500 1.0773 0.02670 0.01921 -0.0103 0.0434 1.0000
9.750 1.0929 0.02800 0.02049 -0.0090 0.0394 1.0000
10.000 1.1085 0.02969 0.02242 -0.0075 0.0361 1.0000
10.250 1.1235 0.03118 0.02409 -0.0059 0.0335 1.0000
10.500 1.1374 0.03269 0.02568 -0.0044 0.0316 1.0000
10.750 1.1472 0.03618 0.02938 -0.0029 0.0296 1.0000
11.000 1.1540 0.03760 0.03111 -0.0004 0.0284 1.0000
11.250 1.1569 0.03949 0.03328 0.0024 0.0272 1.0000
11.500 1.1580 0.04133 0.03532 0.0051 0.0260 1.0000
11.750 1.1561 0.04368 0.03789 0.0076 0.0255 1.0000
12.000 1.1511 0.04616 0.04059 0.0100 0.0249 1.0000
12.250 1.1452 0.04876 0.04337 0.0118 0.0244 1.0000
12.500 1.1354 0.05195 0.04677 0.0131 0.0241 1.0000
12.750 1.1229 0.05559 0.05063 0.0137 0.0240 1.0000
13.000 1.1052 0.06009 0.05539 0.0134 0.0240 1.0000
13.250 1.0876 0.06499 0.06049 0.0120 0.0239 1.0000
13.500 1.0583 0.07218 0.06800 0.0086 0.0243 1.0000
13.750 1.0094 0.08407 0.08026 0.0008 0.0253 1.0000
14.000 0.9484 0.10148 0.09797 -0.0118 0.0270 1.0000
14.250 0.8967 0.11988 0.11643 -0.0234 0.0288 1.0000
14.500 0.8694 0.13243 0.12895 -0.0297 0.0297 1.0000
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Polar data table (+)
Polar graphs
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