RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 100,000 Max Cl/Cd: 48.77 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg149-il-100000.txt Download as CSV file: xf-rg149-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4955 0.09559 0.09056 -0.0190 1.0000 0.1182
-8.750 -0.5055 0.09218 0.08723 -0.0220 1.0000 0.1234
-8.500 -0.5440 0.08853 0.08375 -0.0295 1.0000 0.1251
-8.250 -0.5119 0.08438 0.07958 -0.0239 1.0000 0.1293
-8.000 -0.5121 0.08128 0.07652 -0.0239 1.0000 0.1336
-7.750 -0.5527 0.07719 0.07244 -0.0316 1.0000 0.1392
-7.500 -0.5404 0.07288 0.06822 -0.0292 1.0000 0.1423
-7.250 -0.5317 0.07003 0.06539 -0.0275 1.0000 0.1476
-7.000 -0.5467 0.06566 0.06094 -0.0301 1.0000 0.1560
-6.750 -0.5344 0.06285 0.05818 -0.0278 1.0000 0.1615
-6.500 -0.5347 0.05946 0.05474 -0.0275 1.0000 0.1730
-6.250 -0.5434 0.04264 0.03641 -0.0322 1.0000 0.0809
-6.000 -0.5326 0.03871 0.03214 -0.0306 1.0000 0.0786
-5.750 -0.5201 0.03445 0.02732 -0.0288 1.0000 0.0752
-5.500 -0.5033 0.03107 0.02293 -0.0263 1.0000 0.0707
-5.250 -0.4842 0.02842 0.01989 -0.0247 1.0000 0.0707
-5.000 -0.4650 0.02592 0.01726 -0.0236 1.0000 0.0736
-4.750 -0.4441 0.02448 0.01565 -0.0223 1.0000 0.0778
-4.500 -0.4217 0.02282 0.01369 -0.0209 1.0000 0.0805
-4.250 -0.3987 0.02152 0.01207 -0.0195 1.0000 0.0836
-4.000 -0.3772 0.02003 0.01072 -0.0185 1.0000 0.0911
-3.750 -0.3553 0.01891 0.00956 -0.0172 1.0000 0.1006
-3.500 -0.3340 0.01779 0.00851 -0.0159 1.0000 0.1146
-3.250 -0.3136 0.01672 0.00767 -0.0146 1.0000 0.1469
-3.000 -0.2943 0.01536 0.00690 -0.0133 1.0000 0.2310
-2.750 -0.2786 0.01378 0.00657 -0.0116 1.0000 0.4461
-2.500 -0.2721 0.01280 0.00702 -0.0057 1.0000 0.7534
-2.250 -0.2565 0.01296 0.00732 -0.0011 1.0000 0.8969
-2.000 -0.0980 0.01352 0.00722 -0.0237 1.0000 1.0000
-1.750 -0.1012 0.01342 0.00704 -0.0193 1.0000 1.0000
-1.500 -0.1027 0.01338 0.00691 -0.0151 1.0000 1.0000
-1.250 -0.1005 0.01340 0.00682 -0.0116 1.0000 1.0000
-1.000 -0.0936 0.01349 0.00680 -0.0089 1.0000 1.0000
-0.750 -0.0826 0.01367 0.00686 -0.0070 1.0000 1.0000
-0.500 -0.0561 0.01400 0.00705 -0.0080 0.9966 1.0000
-0.250 -0.0029 0.01447 0.00740 -0.0138 0.9856 1.0000
0.000 0.0489 0.01483 0.00766 -0.0191 0.9737 1.0000
0.250 0.0992 0.01507 0.00783 -0.0240 0.9612 1.0000
0.500 0.1488 0.01523 0.00794 -0.0286 0.9484 1.0000
0.750 0.1987 0.01530 0.00800 -0.0331 0.9356 1.0000
1.000 0.2503 0.01527 0.00798 -0.0377 0.9232 1.0000
1.250 0.3128 0.01506 0.00783 -0.0441 0.9140 1.0000
1.500 0.3626 0.01480 0.00762 -0.0479 0.9001 1.0000
1.750 0.4097 0.01450 0.00738 -0.0510 0.8853 1.0000
2.000 0.4456 0.01426 0.00721 -0.0519 0.8651 1.0000
2.250 0.4835 0.01392 0.00690 -0.0527 0.8442 1.0000
2.500 0.5127 0.01368 0.00667 -0.0518 0.8185 1.0000
2.750 0.5392 0.01352 0.00652 -0.0504 0.7916 1.0000
3.000 0.5638 0.01348 0.00645 -0.0489 0.7651 1.0000
3.250 0.5878 0.01352 0.00645 -0.0473 0.7388 1.0000
3.500 0.6103 0.01361 0.00650 -0.0455 0.7106 1.0000
3.750 0.6316 0.01375 0.00661 -0.0436 0.6799 1.0000
4.000 0.6523 0.01391 0.00672 -0.0416 0.6464 1.0000
4.250 0.6731 0.01411 0.00683 -0.0396 0.6115 1.0000
4.500 0.6932 0.01435 0.00699 -0.0375 0.5735 1.0000
4.750 0.7130 0.01465 0.00719 -0.0355 0.5334 1.0000
5.000 0.7321 0.01501 0.00743 -0.0334 0.4884 1.0000
5.250 0.7500 0.01547 0.00771 -0.0313 0.4370 1.0000
5.500 0.7666 0.01610 0.00809 -0.0290 0.3776 1.0000
5.750 0.7825 0.01697 0.00862 -0.0268 0.3159 1.0000
6.000 0.7988 0.01798 0.00933 -0.0249 0.2640 1.0000
6.250 0.8165 0.01906 0.01017 -0.0232 0.2237 1.0000
6.500 0.8348 0.02021 0.01110 -0.0217 0.1929 1.0000
6.750 0.8545 0.02143 0.01220 -0.0204 0.1682 1.0000
7.000 0.8751 0.02290 0.01344 -0.0195 0.1487 1.0000
7.250 0.8967 0.02431 0.01491 -0.0184 0.1322 1.0000
7.500 0.9183 0.02572 0.01636 -0.0175 0.1180 1.0000
7.750 0.9408 0.02735 0.01795 -0.0167 0.1064 1.0000
8.000 0.9616 0.02868 0.01947 -0.0155 0.0962 1.0000
8.250 0.9823 0.03059 0.02162 -0.0144 0.0873 1.0000
8.500 1.0025 0.03269 0.02377 -0.0136 0.0795 1.0000
8.750 1.0198 0.03455 0.02602 -0.0119 0.0727 1.0000
9.000 1.0360 0.03723 0.02883 -0.0108 0.0669 1.0000
9.250 1.0472 0.03980 0.03195 -0.0084 0.0626 1.0000
9.500 1.0606 0.04246 0.03484 -0.0069 0.0592 1.0000
10.000 1.0674 0.04950 0.04260 -0.0026 0.0546 1.0000
10.250 1.0604 0.05318 0.04679 0.0004 0.0534 1.0000
10.500 1.0489 0.05727 0.05127 0.0031 0.0532 1.0000
10.750 1.0322 0.06117 0.05547 0.0058 0.0533 1.0000
11.000 1.0118 0.06504 0.05956 0.0081 0.0536 1.0000
11.250 0.9903 0.06933 0.06404 0.0090 0.0540 1.0000
11.500 0.9672 0.07428 0.06915 0.0082 0.0544 1.0000
11.750 0.9459 0.07999 0.07497 0.0059 0.0550 1.0000
12.000 0.9244 0.08668 0.08175 0.0024 0.0555 1.0000
12.250 0.6557 0.13446 0.12983 -0.0275 0.1477 1.0000
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Polar data table (+)
Polar graphs
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