NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Reynolds number: 100,000 Max Cl/Cd: 41.52 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc08b3-il-100000-n5.txt Download as CSV file: xf-rc08b3-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-08(B)3 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4829 0.08388 0.07907 -0.0172 1.0000 0.0409
-8.500 -0.5987 0.08361 0.07864 -0.0179 1.0000 0.0421
-8.250 -0.6004 0.07938 0.07441 -0.0187 1.0000 0.0398
-8.000 -0.6152 0.06904 0.06370 -0.0249 1.0000 0.0329
-7.750 -0.6126 0.06500 0.05961 -0.0247 1.0000 0.0322
-7.500 -0.6090 0.06094 0.05543 -0.0244 1.0000 0.0318
-7.250 -0.6045 0.05680 0.05113 -0.0239 1.0000 0.0313
-7.000 -0.5986 0.05267 0.04678 -0.0230 1.0000 0.0309
-6.750 -0.5915 0.04865 0.04247 -0.0217 1.0000 0.0305
-6.500 -0.5831 0.04481 0.03832 -0.0201 1.0000 0.0303
-6.250 -0.5733 0.04128 0.03445 -0.0181 1.0000 0.0301
-6.000 -0.5620 0.03814 0.03090 -0.0159 1.0000 0.0308
-5.750 -0.5493 0.03541 0.02770 -0.0134 1.0000 0.0320
-5.500 -0.5350 0.03303 0.02487 -0.0111 1.0000 0.0325
-5.250 -0.5195 0.03069 0.02216 -0.0089 1.0000 0.0326
-5.000 -0.5025 0.02860 0.01967 -0.0069 1.0000 0.0327
-4.750 -0.4840 0.02677 0.01749 -0.0051 1.0000 0.0329
-4.500 -0.4644 0.02504 0.01549 -0.0035 1.0000 0.0332
-4.250 -0.4441 0.02328 0.01355 -0.0022 1.0000 0.0339
-4.000 -0.4232 0.02196 0.01211 -0.0009 1.0000 0.0348
-3.750 -0.4022 0.02089 0.01096 0.0003 1.0000 0.0360
-3.500 -0.3814 0.02008 0.01006 0.0016 1.0000 0.0383
-3.250 -0.3604 0.01940 0.00928 0.0028 1.0000 0.0418
-3.000 -0.3393 0.01870 0.00848 0.0041 1.0000 0.0441
-2.750 -0.3195 0.01780 0.00761 0.0054 1.0000 0.0469
-2.500 -0.2961 0.01719 0.00697 0.0061 0.9990 0.0516
-2.250 -0.2623 0.01651 0.00624 0.0047 0.9945 0.0623
-2.000 -0.2295 0.01580 0.00572 0.0034 0.9893 0.1010
-1.750 -0.1998 0.01413 0.00539 0.0020 0.9859 0.3746
-1.500 -0.0500 0.01312 0.00596 -0.0192 1.0000 1.0000
-1.250 -0.0408 0.01319 0.00592 -0.0161 1.0000 1.0000
-1.000 -0.0260 0.01326 0.00587 -0.0142 0.9984 1.0000
-0.750 0.0125 0.01328 0.00575 -0.0169 0.9908 1.0000
-0.500 0.0522 0.01330 0.00565 -0.0198 0.9837 1.0000
-0.250 0.0917 0.01330 0.00557 -0.0226 0.9756 1.0000
0.000 0.1317 0.01329 0.00550 -0.0255 0.9673 1.0000
0.250 0.1730 0.01326 0.00544 -0.0285 0.9594 1.0000
0.500 0.2096 0.01323 0.00540 -0.0304 0.9479 1.0000
0.750 0.2455 0.01319 0.00536 -0.0322 0.9355 1.0000
1.000 0.2791 0.01314 0.00533 -0.0333 0.9218 1.0000
1.250 0.3098 0.01309 0.00532 -0.0337 0.9070 1.0000
1.500 0.3387 0.01304 0.00529 -0.0336 0.8911 1.0000
1.750 0.3659 0.01299 0.00527 -0.0331 0.8744 1.0000
2.000 0.3907 0.01296 0.00530 -0.0321 0.8558 1.0000
2.250 0.4146 0.01293 0.00532 -0.0309 0.8355 1.0000
2.500 0.4383 0.01288 0.00530 -0.0295 0.8128 1.0000
2.750 0.4616 0.01285 0.00529 -0.0279 0.7869 1.0000
3.000 0.4842 0.01284 0.00533 -0.0263 0.7558 1.0000
3.250 0.5065 0.01286 0.00532 -0.0245 0.7164 1.0000
3.500 0.5280 0.01294 0.00528 -0.0225 0.6596 1.0000
3.750 0.5485 0.01321 0.00524 -0.0203 0.5764 1.0000
4.000 0.5674 0.01379 0.00534 -0.0182 0.4734 1.0000
4.250 0.5857 0.01460 0.00567 -0.0165 0.3695 1.0000
4.500 0.6042 0.01549 0.00610 -0.0151 0.2734 1.0000
4.750 0.6228 0.01645 0.00663 -0.0138 0.1877 1.0000
5.000 0.6414 0.01747 0.00726 -0.0125 0.1227 1.0000
5.250 0.6607 0.01840 0.00801 -0.0112 0.0916 1.0000
5.500 0.6799 0.01932 0.00885 -0.0098 0.0746 1.0000
5.750 0.6996 0.02013 0.00972 -0.0084 0.0648 1.0000
6.000 0.7183 0.02110 0.01075 -0.0068 0.0591 1.0000
6.250 0.7375 0.02199 0.01170 -0.0054 0.0535 1.0000
6.500 0.7556 0.02309 0.01280 -0.0039 0.0489 1.0000
6.750 0.7753 0.02415 0.01401 -0.0025 0.0458 1.0000
7.000 0.7950 0.02537 0.01539 -0.0011 0.0433 1.0000
7.250 0.8149 0.02670 0.01680 0.0002 0.0413 1.0000
7.500 0.8344 0.02832 0.01848 0.0014 0.0395 1.0000
7.750 0.8539 0.03007 0.02044 0.0027 0.0373 1.0000
8.000 0.8729 0.03164 0.02235 0.0041 0.0349 1.0000
8.250 0.8906 0.03373 0.02476 0.0056 0.0336 1.0000
8.500 0.9063 0.03601 0.02742 0.0073 0.0324 1.0000
8.750 0.9196 0.03840 0.03015 0.0091 0.0314 1.0000
9.000 0.9317 0.04040 0.03238 0.0107 0.0300 1.0000
9.250 0.9404 0.04314 0.03525 0.0123 0.0285 1.0000
9.500 0.9429 0.04610 0.03874 0.0149 0.0275 1.0000
9.750 0.9412 0.04967 0.04279 0.0175 0.0270 1.0000
10.000 0.9344 0.05350 0.04703 0.0201 0.0267 1.0000
10.250 0.9224 0.05743 0.05130 0.0225 0.0265 1.0000
10.500 0.9046 0.06115 0.05527 0.0250 0.0265 1.0000
10.750 0.8841 0.06526 0.05959 0.0261 0.0265 1.0000
11.000 0.8624 0.07026 0.06476 0.0251 0.0266 1.0000
11.250 0.8399 0.07650 0.07115 0.0216 0.0268 1.0000
11.500 0.8174 0.08454 0.07928 0.0158 0.0271 1.0000
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Polar data table (+)
Polar graphs
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