NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 200,000 Max Cl/Cd: 55.68 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf414f-il-200000.txt Download as CSV file: xf-nlf414f-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2103 0.10264 0.09902 -0.0843 0.9147 0.0529
-11.250 -0.2066 0.09907 0.09546 -0.0860 0.9149 0.0544
-11.000 -0.3494 0.10059 0.09688 -0.0830 0.9132 0.0506
-10.750 -0.3357 0.09860 0.09488 -0.0823 0.9133 0.0515
-10.500 -0.3274 0.09553 0.09181 -0.0838 0.9134 0.0527
-10.250 -0.3231 0.09158 0.08787 -0.0867 0.9135 0.0541
-10.000 -0.3234 0.08643 0.08273 -0.0915 0.9136 0.0558
-9.750 -0.3347 0.07859 0.07488 -0.1007 0.9133 0.0571
-9.500 -0.3571 0.07216 0.06832 -0.1079 0.9130 0.0581
-9.250 -0.3909 0.06915 0.06503 -0.1106 0.9131 0.0591
-9.000 -0.4158 0.06826 0.06373 -0.1097 0.9132 0.0596
-8.750 -0.4115 0.06185 0.05743 -0.1103 0.9128 0.0609
-8.500 -0.6912 0.08865 0.08531 -0.0360 1.0000 0.0494
-8.250 -0.7174 0.08541 0.08183 -0.0339 1.0000 0.0496
-8.000 -0.7327 0.08242 0.07857 -0.0319 1.0000 0.0497
-7.750 -0.7255 0.07567 0.07206 -0.0317 1.0000 0.0506
-7.500 -0.7211 0.07282 0.06925 -0.0305 1.0000 0.0513
-7.250 -0.7183 0.07011 0.06650 -0.0292 1.0000 0.0521
-7.000 -0.7150 0.06735 0.06366 -0.0281 1.0000 0.0532
-6.750 -0.7107 0.06436 0.06052 -0.0272 1.0000 0.0549
-6.500 -0.7083 0.06028 0.05554 -0.0273 0.9993 0.0604
-4.500 -0.4708 0.03312 0.02552 -0.0388 0.9739 0.0392
-4.250 -0.4369 0.03160 0.02373 -0.0400 0.9726 0.0376
-4.000 -0.4088 0.03036 0.02228 -0.0400 0.9661 0.0371
-3.750 -0.3763 0.02959 0.02140 -0.0411 0.9626 0.0374
-3.500 -0.3419 0.02916 0.02090 -0.0426 0.9603 0.0384
-3.250 -0.3055 0.02929 0.02096 -0.0446 0.9587 0.0409
-3.000 -0.2820 0.02826 0.02002 -0.0444 0.9493 0.0436
-2.750 -0.2467 0.02812 0.01990 -0.0464 0.9467 0.0473
-2.500 -0.2083 0.02802 0.01984 -0.0493 0.9450 0.0538
-2.250 -0.1672 0.02819 0.02012 -0.0527 0.9439 0.0790
-2.000 -0.1500 0.02597 0.02084 -0.0515 0.9346 0.7329
-1.750 -0.1241 0.02791 0.02274 -0.0494 0.9304 0.7767
-1.500 -0.1140 0.02840 0.02324 -0.0445 0.9184 0.7987
-1.250 -0.0945 0.02973 0.02458 -0.0409 0.9151 0.8248
-1.000 -0.0926 0.02969 0.02455 -0.0342 0.9027 0.8501
-0.750 -0.0947 0.02978 0.02467 -0.0263 0.8927 0.8750
-0.500 -0.0822 0.02997 0.02484 -0.0215 0.8869 0.8977
-0.250 -0.0674 0.02993 0.02474 -0.0190 0.8762 0.9066
0.000 -0.0267 0.03055 0.02525 -0.0219 0.8715 0.9094
0.250 -0.0024 0.03043 0.02507 -0.0212 0.8586 0.9128
0.500 0.0488 0.02987 0.02438 -0.0233 0.8307 0.9145
0.750 0.0928 0.03012 0.02455 -0.0261 0.8261 0.9158
1.000 0.1120 0.03001 0.02441 -0.0251 0.8152 0.9181
1.250 0.1518 0.03020 0.02455 -0.0274 0.8115 0.9190
1.500 0.1951 0.03058 0.02489 -0.0301 0.8089 0.9197
1.750 0.2084 0.03038 0.02469 -0.0287 0.7977 0.9216
2.000 0.2491 0.03057 0.02486 -0.0311 0.7951 0.9222
2.250 0.2664 0.03066 0.02496 -0.0304 0.7849 0.9237
2.500 0.3034 0.03074 0.02504 -0.0322 0.7813 0.9241
2.750 0.3439 0.03083 0.02514 -0.0344 0.7792 0.9245
3.000 0.3603 0.03096 0.02529 -0.0337 0.7686 0.9257
3.250 0.3987 0.03086 0.02522 -0.0355 0.7653 0.9260
3.500 0.4406 0.03071 0.02511 -0.0376 0.7634 0.9260
3.750 0.4578 0.03072 0.02516 -0.0368 0.7522 0.9269
4.000 0.5038 0.02993 0.02443 -0.0388 0.7493 0.9272
4.250 0.5336 0.02911 0.02366 -0.0388 0.7383 0.9280
4.500 0.5874 0.02730 0.02190 -0.0410 0.7349 0.9278
4.750 0.6135 0.02677 0.02145 -0.0408 0.7243 0.9283
5.000 0.6619 0.02507 0.01984 -0.0425 0.7211 0.9282
5.250 0.6922 0.02396 0.01881 -0.0424 0.7090 0.9286
5.500 0.7229 0.02292 0.01787 -0.0424 0.6965 0.9291
5.750 0.7529 0.02193 0.01699 -0.0422 0.6827 0.9300
6.000 0.7830 0.02090 0.01605 -0.0420 0.6656 0.9308
6.250 0.8173 0.01961 0.01481 -0.0421 0.6351 0.9312
6.500 0.8769 0.01575 0.00998 -0.0412 0.4802 0.9306
6.750 0.8697 0.01773 0.01121 -0.0375 0.3592 0.9316
7.000 0.8638 0.01985 0.01265 -0.0343 0.2480 0.9326
7.250 0.8660 0.02160 0.01387 -0.0320 0.1710 0.9339
7.500 0.8751 0.02300 0.01496 -0.0304 0.1276 0.9350
7.750 0.8874 0.02426 0.01603 -0.0292 0.1035 0.9356
8.000 0.9022 0.02537 0.01706 -0.0282 0.0900 0.9361
8.250 0.9179 0.02643 0.01806 -0.0273 0.0814 0.9366
8.500 0.9354 0.02738 0.01905 -0.0266 0.0754 0.9373
8.750 0.9529 0.02832 0.01995 -0.0258 0.0703 0.9384
9.000 0.9712 0.02936 0.02100 -0.0250 0.0662 0.9393
9.250 0.9921 0.03021 0.02190 -0.0246 0.0630 0.9399
9.500 1.0135 0.03110 0.02278 -0.0242 0.0602 0.9405
9.750 1.0419 0.03227 0.02386 -0.0241 0.0572 0.9409
10.000 1.0645 0.03309 0.02484 -0.0238 0.0553 0.9417
10.250 1.0886 0.03402 0.02587 -0.0236 0.0532 0.9425
10.500 1.1144 0.03506 0.02698 -0.0235 0.0515 0.9435
10.750 1.1421 0.03622 0.02819 -0.0237 0.0500 0.9445
11.000 1.1886 0.03867 0.03068 -0.0258 0.0480 0.9447
11.250 1.2034 0.03996 0.03224 -0.0247 0.0472 0.9465
11.500 1.2198 0.04160 0.03416 -0.0238 0.0462 0.9484
11.750 1.2367 0.04368 0.03651 -0.0230 0.0454 0.9507
12.000 1.2500 0.04604 0.03917 -0.0218 0.0449 0.9542
12.250 1.2586 0.04867 0.04212 -0.0203 0.0445 0.9601
12.500 1.2616 0.05157 0.04535 -0.0184 0.0444 0.9765
12.750 1.2601 0.05487 0.04898 -0.0165 0.0443 1.0000
13.000 1.2531 0.05842 0.05285 -0.0144 0.0442 1.0000
13.250 1.2411 0.06224 0.05698 -0.0122 0.0443 1.0000
13.500 1.2242 0.06643 0.06147 -0.0101 0.0444 1.0000
13.750 1.2034 0.07106 0.06640 -0.0083 0.0446 1.0000
14.000 1.1791 0.07617 0.07178 -0.0070 0.0449 1.0000
14.250 1.1521 0.08180 0.07766 -0.0064 0.0453 1.0000
14.500 1.1233 0.08800 0.08409 -0.0067 0.0458 1.0000
14.750 1.0937 0.09486 0.09115 -0.0082 0.0463 1.0000
15.000 1.0653 0.10239 0.09885 -0.0109 0.0468 1.0000
15.250 1.0414 0.11035 0.10693 -0.0143 0.0474 1.0000
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