LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il) Reynolds number: 500,000 Max Cl/Cd: 111.05 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l7769-il-500000-n5.txt Download as CSV file: xf-l7769-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LISSAMAN 7769 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4546 0.11028 0.10623 0.0145 0.4942 0.0211
-10.000 -0.4495 0.10685 0.10280 0.0128 0.4927 0.0214
-8.500 -0.6320 0.03222 0.02727 -0.0348 0.4943 0.0249
-8.250 -0.6150 0.02881 0.02350 -0.0354 0.4924 0.0252
-8.000 -0.5949 0.02641 0.02078 -0.0354 0.4902 0.0254
-7.750 -0.5727 0.02459 0.01868 -0.0353 0.4880 0.0257
-7.500 -0.5494 0.02309 0.01694 -0.0351 0.4857 0.0259
-7.250 -0.5251 0.02181 0.01543 -0.0348 0.4836 0.0262
-7.000 -0.5002 0.02071 0.01410 -0.0346 0.4814 0.0264
-6.750 -0.4748 0.01973 0.01292 -0.0343 0.4792 0.0267
-6.500 -0.4488 0.01884 0.01187 -0.0340 0.4770 0.0269
-6.250 -0.4225 0.01805 0.01092 -0.0337 0.4748 0.0272
-6.000 -0.3958 0.01736 0.01008 -0.0334 0.4726 0.0275
-5.750 -0.3688 0.01679 0.00938 -0.0331 0.4705 0.0278
-5.500 -0.3416 0.01630 0.00876 -0.0328 0.4684 0.0282
-5.250 -0.3143 0.01581 0.00814 -0.0325 0.4664 0.0283
-5.000 -0.2872 0.01527 0.00748 -0.0322 0.4646 0.0286
-4.750 -0.2602 0.01461 0.00674 -0.0319 0.4628 0.0289
-4.500 -0.2328 0.01412 0.00621 -0.0316 0.4610 0.0293
-4.250 -0.2052 0.01371 0.00576 -0.0314 0.4590 0.0297
-4.000 -0.1774 0.01336 0.00538 -0.0311 0.4568 0.0300
-3.750 -0.1496 0.01305 0.00502 -0.0309 0.4546 0.0304
-3.500 -0.1217 0.01276 0.00469 -0.0306 0.4527 0.0309
-3.250 -0.0938 0.01250 0.00439 -0.0304 0.4509 0.0314
-3.000 -0.0658 0.01226 0.00410 -0.0301 0.4492 0.0319
-2.750 -0.0378 0.01206 0.00385 -0.0299 0.4474 0.0324
-2.500 -0.0096 0.01187 0.00363 -0.0297 0.4459 0.0330
-2.250 0.0187 0.01170 0.00344 -0.0295 0.4443 0.0337
-2.000 0.0468 0.01146 0.00321 -0.0293 0.4426 0.0349
-1.750 0.0750 0.01129 0.00303 -0.0291 0.4408 0.0360
-1.500 0.1033 0.01114 0.00288 -0.0289 0.4390 0.0372
-1.250 0.1316 0.01102 0.00273 -0.0287 0.4371 0.0387
-1.000 0.1599 0.01090 0.00260 -0.0286 0.4353 0.0411
-0.750 0.1881 0.01077 0.00249 -0.0284 0.4336 0.0463
-0.500 0.2162 0.01064 0.00242 -0.0282 0.4320 0.0626
-0.250 0.2445 0.01057 0.00240 -0.0281 0.4306 0.0773
0.000 0.2729 0.01051 0.00239 -0.0280 0.4292 0.0879
0.250 0.3014 0.01047 0.00240 -0.0279 0.4276 0.0976
0.500 0.3299 0.01044 0.00241 -0.0278 0.4260 0.1062
0.750 0.3584 0.01043 0.00242 -0.0276 0.4245 0.1141
1.000 0.3869 0.01042 0.00244 -0.0275 0.4229 0.1220
1.250 0.4154 0.01042 0.00245 -0.0274 0.4212 0.1287
1.500 0.4438 0.01041 0.00246 -0.0273 0.4195 0.1371
1.750 0.4722 0.01041 0.00248 -0.0273 0.4179 0.1456
2.000 0.5005 0.01043 0.00250 -0.0272 0.4164 0.1536
2.250 0.5289 0.01045 0.00255 -0.0271 0.4151 0.1609
2.500 0.5573 0.01045 0.00260 -0.0270 0.4138 0.1694
2.750 0.5857 0.01045 0.00266 -0.0270 0.4124 0.1804
3.000 0.6140 0.01042 0.00273 -0.0269 0.4106 0.2015
3.500 0.6781 0.00861 0.00290 -0.0287 0.4058 1.0000
3.750 0.7059 0.00869 0.00294 -0.0285 0.4033 1.0000
4.000 0.7336 0.00879 0.00299 -0.0283 0.4009 1.0000
4.250 0.7615 0.00888 0.00308 -0.0282 0.3986 1.0000
4.500 0.7894 0.00895 0.00318 -0.0280 0.3955 1.0000
4.750 0.8174 0.00902 0.00326 -0.0279 0.3923 1.0000
5.000 0.8452 0.00912 0.00335 -0.0278 0.3899 1.0000
5.250 0.8729 0.00922 0.00344 -0.0276 0.3872 1.0000
5.500 0.9007 0.00931 0.00353 -0.0275 0.3832 1.0000
5.750 0.9287 0.00937 0.00364 -0.0274 0.3779 1.0000
6.000 0.9564 0.00947 0.00374 -0.0273 0.3736 1.0000
6.250 0.9839 0.00960 0.00386 -0.0272 0.3705 1.0000
6.500 1.0118 0.00971 0.00403 -0.0271 0.3666 1.0000
6.750 1.0394 0.00982 0.00417 -0.0270 0.3617 1.0000
7.000 1.0669 0.00995 0.00431 -0.0269 0.3571 1.0000
7.250 1.0944 0.01009 0.00450 -0.0268 0.3525 1.0000
7.500 1.1219 0.01023 0.00468 -0.0268 0.3465 1.0000
7.750 1.1490 0.01040 0.00486 -0.0267 0.3398 1.0000
8.000 1.1760 0.01059 0.00506 -0.0266 0.3279 1.0000
8.250 1.2022 0.01088 0.00532 -0.0265 0.3075 1.0000
8.500 1.2267 0.01143 0.00574 -0.0263 0.2771 1.0000
8.750 1.2496 0.01223 0.00639 -0.0261 0.2461 1.0000
9.000 1.2719 0.01309 0.00714 -0.0259 0.2204 1.0000
9.250 1.2948 0.01383 0.00783 -0.0257 0.2022 1.0000
9.500 1.3174 0.01457 0.00852 -0.0255 0.1860 1.0000
9.750 1.3384 0.01548 0.00934 -0.0253 0.1665 1.0000
10.000 1.3581 0.01649 0.01027 -0.0250 0.1443 1.0000
10.250 1.3762 0.01762 0.01131 -0.0247 0.1258 1.0000
10.500 1.3947 0.01863 0.01229 -0.0244 0.1134 1.0000
10.750 1.4122 0.01968 0.01334 -0.0241 0.1027 1.0000
11.000 1.4270 0.02095 0.01460 -0.0238 0.0918 1.0000
11.250 1.4370 0.02265 0.01630 -0.0236 0.0796 1.0000
11.500 1.4365 0.02625 0.01993 -0.0256 0.0671 1.0000
11.750 1.4197 0.03030 0.02403 -0.0258 0.0622 1.0000
12.000 1.4049 0.03409 0.02782 -0.0258 0.0554 1.0000
12.250 1.3914 0.03777 0.03150 -0.0257 0.0479 1.0000
12.500 1.3807 0.04124 0.03497 -0.0257 0.0412 1.0000
12.750 1.3697 0.04480 0.03853 -0.0258 0.0346 1.0000
13.000 1.3618 0.04812 0.04185 -0.0260 0.0295 1.0000
13.250 1.3563 0.05126 0.04501 -0.0262 0.0258 1.0000
13.500 1.3529 0.05434 0.04812 -0.0265 0.0234 1.0000
13.750 1.3525 0.05722 0.05105 -0.0269 0.0213 1.0000
14.000 1.3505 0.06038 0.05424 -0.0274 0.0195 1.0000
14.250 1.3519 0.06321 0.05713 -0.0279 0.0185 1.0000
14.500 1.3528 0.06616 0.06013 -0.0284 0.0176 1.0000
14.750 1.3531 0.06924 0.06327 -0.0291 0.0169 1.0000
15.000 1.3524 0.07252 0.06660 -0.0298 0.0161 1.0000
15.250 1.3519 0.07582 0.06997 -0.0306 0.0155 1.0000
15.500 1.3533 0.07892 0.07315 -0.0314 0.0151 1.0000
15.750 1.3532 0.08231 0.07662 -0.0324 0.0147 1.0000
16.000 1.3532 0.08568 0.08006 -0.0333 0.0142 1.0000
16.250 1.3518 0.08937 0.08382 -0.0345 0.0139 1.0000
16.500 1.3500 0.09315 0.08767 -0.0357 0.0135 1.0000
16.750 1.3471 0.09721 0.09180 -0.0371 0.0132 1.0000
17.000 1.3429 0.10149 0.09616 -0.0387 0.0128 1.0000
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