FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 500,000 Max Cl/Cd: 82.65 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fauvel-il-500000-n5.txt Download as CSV file: xf-fauvel-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FAUVEL 14% 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9746 0.05785 0.05384 -0.0271 0.6732 0.0183
-14.000 -1.0092 0.05101 0.04672 -0.0298 0.6669 0.0183
-13.750 -1.0324 0.04652 0.04199 -0.0298 0.6598 0.0184
-13.500 -1.0451 0.04352 0.03878 -0.0286 0.6538 0.0185
-13.250 -1.0570 0.04079 0.03583 -0.0267 0.6485 0.0187
-13.000 -1.0647 0.03855 0.03339 -0.0242 0.6434 0.0189
-12.750 -1.0711 0.03647 0.03107 -0.0212 0.6382 0.0191
-12.500 -1.0733 0.03472 0.02911 -0.0182 0.6333 0.0193
-12.250 -1.0734 0.03311 0.02728 -0.0150 0.6285 0.0195
-12.000 -1.0710 0.03169 0.02563 -0.0117 0.6237 0.0198
-11.750 -1.0658 0.03048 0.02420 -0.0086 0.6199 0.0200
-11.500 -1.0571 0.02936 0.02295 -0.0060 0.6164 0.0202
-11.250 -1.0431 0.02852 0.02204 -0.0040 0.6127 0.0204
-11.000 -1.0274 0.02779 0.02124 -0.0023 0.6089 0.0206
-10.750 -1.0100 0.02723 0.02060 -0.0007 0.6055 0.0208
-10.500 -0.9919 0.02663 0.01994 0.0008 0.6023 0.0210
-10.250 -0.9730 0.02603 0.01927 0.0022 0.5989 0.0213
-10.000 -0.9539 0.02536 0.01851 0.0036 0.5953 0.0217
-9.750 -0.9344 0.02463 0.01765 0.0050 0.5916 0.0220
-9.500 -0.9145 0.02386 0.01674 0.0063 0.5883 0.0224
-9.250 -0.8936 0.02309 0.01585 0.0075 0.5851 0.0227
-9.000 -0.8721 0.02237 0.01501 0.0087 0.5812 0.0231
-8.750 -0.8499 0.02173 0.01423 0.0098 0.5775 0.0234
-8.500 -0.8273 0.02114 0.01351 0.0108 0.5737 0.0236
-8.250 -0.8051 0.02036 0.01269 0.0118 0.5702 0.0240
-8.000 -0.7818 0.01983 0.01216 0.0127 0.5664 0.0244
-7.750 -0.7580 0.01935 0.01164 0.0135 0.5619 0.0248
-7.500 -0.7341 0.01889 0.01113 0.0144 0.5574 0.0252
-7.250 -0.7100 0.01840 0.01057 0.0152 0.5534 0.0255
-7.000 -0.6855 0.01790 0.01003 0.0160 0.5491 0.0259
-6.750 -0.6609 0.01743 0.00950 0.0168 0.5442 0.0264
-6.500 -0.6363 0.01698 0.00898 0.0176 0.5391 0.0267
-6.250 -0.6112 0.01657 0.00851 0.0184 0.5337 0.0272
-6.000 -0.5858 0.01624 0.00811 0.0190 0.5274 0.0275
-5.750 -0.5619 0.01566 0.00752 0.0199 0.5217 0.0281
-5.500 -0.5372 0.01524 0.00709 0.0207 0.5155 0.0286
-5.250 -0.5122 0.01487 0.00669 0.0214 0.5081 0.0290
-5.000 -0.4870 0.01453 0.00632 0.0222 0.5004 0.0295
-4.750 -0.4617 0.01420 0.00596 0.0229 0.4914 0.0300
-4.500 -0.4362 0.01391 0.00561 0.0236 0.4830 0.0305
-4.250 -0.4107 0.01363 0.00529 0.0243 0.4742 0.0310
-4.000 -0.3849 0.01339 0.00500 0.0249 0.4662 0.0316
-3.750 -0.3592 0.01315 0.00471 0.0256 0.4575 0.0322
-3.500 -0.3340 0.01286 0.00440 0.0263 0.4493 0.0330
-3.250 -0.3081 0.01265 0.00416 0.0269 0.4408 0.0338
-3.000 -0.2821 0.01247 0.00393 0.0275 0.4334 0.0346
-2.750 -0.2557 0.01229 0.00373 0.0281 0.4268 0.0355
-2.500 -0.2294 0.01215 0.00355 0.0286 0.4202 0.0364
-2.250 -0.2030 0.01200 0.00337 0.0292 0.4143 0.0375
-2.000 -0.1767 0.01184 0.00320 0.0297 0.4080 0.0392
-1.750 -0.1502 0.01172 0.00306 0.0303 0.4017 0.0417
-1.500 -0.1238 0.01159 0.00293 0.0308 0.3967 0.0458
-1.250 -0.0977 0.01141 0.00282 0.0313 0.3918 0.0580
-1.000 -0.0721 0.01121 0.00272 0.0320 0.3868 0.0853
-0.750 -0.0466 0.01104 0.00261 0.0326 0.3819 0.1136
-0.500 -0.0233 0.01063 0.00253 0.0335 0.3776 0.1975
-0.250 0.0020 0.01043 0.00248 0.0341 0.3727 0.2489
0.000 0.0276 0.01027 0.00243 0.0347 0.3683 0.2863
0.250 0.0517 0.01001 0.00237 0.0355 0.3643 0.3497
0.500 0.0602 0.00877 0.00217 0.0392 0.3615 0.6375
0.750 0.0815 0.00849 0.00219 0.0409 0.3578 0.7175
1.000 0.1056 0.00837 0.00223 0.0420 0.3536 0.7693
1.250 0.1307 0.00832 0.00232 0.0430 0.3494 0.8155
1.500 0.1575 0.00836 0.00241 0.0436 0.3457 0.8450
1.750 0.1856 0.00839 0.00251 0.0440 0.3426 0.8682
2.000 0.2140 0.00846 0.00259 0.0442 0.3392 0.8819
2.250 0.2425 0.00854 0.00266 0.0444 0.3353 0.8920
2.500 0.2715 0.00864 0.00273 0.0444 0.3315 0.9002
2.750 0.3006 0.00875 0.00282 0.0444 0.3280 0.9075
3.000 0.3289 0.00882 0.00289 0.0445 0.3252 0.9141
3.250 0.3603 0.00892 0.00299 0.0440 0.3219 0.9195
3.500 0.3892 0.00903 0.00308 0.0440 0.3187 0.9255
3.750 0.4185 0.00915 0.00318 0.0438 0.3152 0.9309
4.000 0.4507 0.00931 0.00331 0.0430 0.3117 0.9354
4.250 0.4799 0.00941 0.00342 0.0429 0.3089 0.9414
4.500 0.5104 0.00952 0.00354 0.0425 0.3056 0.9454
4.750 0.5435 0.00965 0.00367 0.0415 0.3017 0.9483
5.000 0.5753 0.00983 0.00381 0.0408 0.2971 0.9528
5.250 0.6040 0.00996 0.00394 0.0407 0.2930 0.9583
5.500 0.6383 0.01009 0.00409 0.0394 0.2889 0.9601
5.750 0.6715 0.01025 0.00423 0.0383 0.2836 0.9619
6.000 0.7038 0.01043 0.00438 0.0373 0.2787 0.9640
6.250 0.7350 0.01056 0.00453 0.0366 0.2749 0.9668
6.500 0.7626 0.01070 0.00470 0.0367 0.2711 0.9706
6.750 0.7962 0.01089 0.00487 0.0354 0.2664 0.9718
7.000 0.8292 0.01107 0.00505 0.0342 0.2621 0.9733
7.250 0.8617 0.01122 0.00524 0.0332 0.2579 0.9751
7.500 0.8930 0.01141 0.00544 0.0323 0.2527 0.9774
7.750 0.9222 0.01164 0.00565 0.0319 0.2469 0.9803
8.000 0.9518 0.01183 0.00586 0.0313 0.2395 0.9828
8.250 0.9841 0.01209 0.00611 0.0301 0.2320 0.9842
8.500 1.0157 0.01235 0.00635 0.0290 0.2222 0.9859
8.750 1.0463 0.01266 0.00665 0.0281 0.2118 0.9880
9.000 1.0754 0.01307 0.00701 0.0273 0.1974 0.9904
9.250 1.1030 0.01356 0.00744 0.0267 0.1823 0.9929
9.500 1.1326 0.01408 0.00791 0.0256 0.1681 0.9947
9.750 1.1617 0.01468 0.00846 0.0245 0.1537 0.9969
10.000 1.1904 0.01533 0.00906 0.0234 0.1412 0.9989
10.250 1.2141 0.01597 0.00968 0.0232 0.1316 1.0000
10.500 1.2281 0.01660 0.01029 0.0250 0.1244 1.0000
10.750 1.2423 0.01717 0.01087 0.0268 0.1187 1.0000
11.000 1.2544 0.01786 0.01157 0.0287 0.1128 1.0000
11.250 1.2668 0.01851 0.01223 0.0306 0.1086 1.0000
11.500 1.2781 0.01919 0.01295 0.0325 0.1042 1.0000
11.750 1.2860 0.02006 0.01383 0.0346 0.1002 1.0000
12.000 1.2934 0.02094 0.01475 0.0366 0.0969 1.0000
12.250 1.2942 0.02200 0.01587 0.0393 0.0938 1.0000
12.500 1.2848 0.02439 0.01834 0.0403 0.0910 1.0000
12.750 1.2801 0.02717 0.02118 0.0400 0.0882 1.0000
13.000 1.2793 0.02948 0.02355 0.0400 0.0854 1.0000
13.250 1.2754 0.03211 0.02622 0.0400 0.0820 1.0000
13.500 1.2684 0.03507 0.02922 0.0398 0.0791 1.0000
13.750 1.2636 0.03791 0.03212 0.0396 0.0762 1.0000
14.000 1.2575 0.04096 0.03522 0.0392 0.0730 1.0000
14.250 1.2486 0.04441 0.03871 0.0386 0.0702 1.0000
14.500 1.2416 0.04773 0.04208 0.0379 0.0675 1.0000
14.750 1.2342 0.05118 0.04559 0.0372 0.0648 1.0000
15.000 1.2250 0.05504 0.04948 0.0361 0.0620 1.0000
15.250 1.2194 0.05858 0.05307 0.0351 0.0596 1.0000
15.500 1.2136 0.06219 0.05674 0.0340 0.0574 1.0000
15.750 1.2045 0.06628 0.06087 0.0327 0.0550 1.0000
16.000 1.1983 0.07008 0.06472 0.0315 0.0533 1.0000
16.250 1.1939 0.07368 0.06838 0.0303 0.0516 1.0000
16.500 1.1887 0.07743 0.07218 0.0290 0.0502 1.0000
16.750 1.1804 0.08167 0.07646 0.0275 0.0486 1.0000
17.000 1.1757 0.08546 0.08030 0.0262 0.0475 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FAUVEL 14% AIRFOIL (fauvel-il)