NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 500,000 Max Cl/Cd: 81.94 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0115-il-500000.txt Download as CSV file: xf-nlf0115-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NLF(1)-0115
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4112 0.12173 0.11928 -0.0436 1.0000 0.0225
-12.500 -0.4115 0.11826 0.11582 -0.0443 1.0000 0.0230
-7.250 -0.4353 0.02353 0.01796 -0.0709 0.9191 0.0274
-7.000 -0.4034 0.01967 0.01347 -0.0703 0.9088 0.0213
-6.750 -0.3736 0.01856 0.01224 -0.0707 0.8952 0.0211
-6.500 -0.3430 0.01713 0.01067 -0.0712 0.8805 0.0212
-6.250 -0.3153 0.01588 0.00933 -0.0712 0.8645 0.0214
-6.000 -0.2917 0.01507 0.00841 -0.0705 0.8485 0.0217
-5.750 -0.2708 0.01441 0.00768 -0.0694 0.8341 0.0222
-5.500 -0.2502 0.01392 0.00711 -0.0682 0.8215 0.0227
-5.250 -0.2299 0.01349 0.00660 -0.0669 0.8102 0.0232
-5.000 -0.2096 0.01308 0.00613 -0.0657 0.8002 0.0237
-4.500 -0.1660 0.01245 0.00538 -0.0637 0.7841 0.0258
-4.250 -0.1458 0.01201 0.00485 -0.0624 0.7774 0.0269
-4.000 -0.1238 0.01166 0.00449 -0.0615 0.7711 0.0285
-3.750 -0.1002 0.01141 0.00420 -0.0608 0.7652 0.0307
-3.250 -0.0545 0.01076 0.00359 -0.0591 0.7548 0.0581
-3.000 -0.0439 0.00948 0.00312 -0.0568 0.7495 0.2600
-2.750 -0.0407 0.00798 0.00289 -0.0529 0.7450 0.6250
-2.500 -0.0139 0.00821 0.00310 -0.0524 0.7411 0.6535
-2.250 0.0131 0.00845 0.00333 -0.0520 0.7371 0.6714
-2.000 0.0406 0.00868 0.00356 -0.0517 0.7335 0.6844
-1.750 0.0685 0.00894 0.00380 -0.0514 0.7301 0.6962
-1.500 0.0958 0.00930 0.00418 -0.0508 0.7268 0.7108
-1.250 0.1232 0.00957 0.00444 -0.0505 0.7233 0.7208
-1.000 0.1511 0.00956 0.00443 -0.0505 0.7202 0.7245
-0.750 0.1797 0.00954 0.00438 -0.0507 0.7172 0.7258
-0.500 0.2085 0.00954 0.00431 -0.0511 0.7144 0.7267
-0.250 0.2374 0.00955 0.00427 -0.0515 0.7115 0.7275
0.000 0.2655 0.00953 0.00424 -0.0517 0.7086 0.7284
0.250 0.2933 0.00950 0.00419 -0.0518 0.7041 0.7295
0.500 0.3213 0.00948 0.00409 -0.0518 0.6974 0.7306
0.750 0.3475 0.00941 0.00400 -0.0515 0.6890 0.7316
1.000 0.3751 0.00939 0.00389 -0.0515 0.6811 0.7326
1.250 0.4015 0.00934 0.00384 -0.0513 0.6738 0.7336
1.500 0.4291 0.00932 0.00379 -0.0514 0.6683 0.7345
1.750 0.4572 0.00934 0.00376 -0.0515 0.6632 0.7355
2.000 0.4842 0.00932 0.00376 -0.0515 0.6577 0.7365
2.250 0.5116 0.00931 0.00373 -0.0515 0.6520 0.7376
2.500 0.5390 0.00929 0.00371 -0.0515 0.6465 0.7387
2.750 0.5657 0.00925 0.00370 -0.0513 0.6402 0.7396
3.000 0.5928 0.00926 0.00369 -0.0512 0.6335 0.7406
3.250 0.6188 0.00923 0.00371 -0.0509 0.6257 0.7417
3.500 0.6453 0.00925 0.00371 -0.0507 0.6181 0.7429
3.750 0.6708 0.00923 0.00374 -0.0503 0.6080 0.7441
4.000 0.6962 0.00924 0.00375 -0.0499 0.5972 0.7454
4.250 0.7210 0.00926 0.00376 -0.0494 0.5848 0.7467
4.500 0.7451 0.00929 0.00380 -0.0487 0.5683 0.7482
4.750 0.7670 0.00936 0.00382 -0.0476 0.5406 0.7496
5.000 0.7828 0.00963 0.00387 -0.0453 0.4850 0.7513
5.250 0.7901 0.01033 0.00417 -0.0415 0.4088 0.7530
5.500 0.7999 0.01098 0.00453 -0.0384 0.3496 0.7548
5.750 0.8119 0.01154 0.00490 -0.0357 0.3048 0.7564
6.000 0.8254 0.01200 0.00521 -0.0332 0.2722 0.7582
6.250 0.8385 0.01241 0.00551 -0.0307 0.2478 0.7601
6.500 0.8533 0.01278 0.00580 -0.0285 0.2292 0.7622
6.750 0.8688 0.01316 0.00613 -0.0265 0.2131 0.7644
7.000 0.8846 0.01356 0.00648 -0.0245 0.1993 0.7666
7.250 0.9007 0.01397 0.00683 -0.0227 0.1874 0.7688
7.500 0.9180 0.01430 0.00717 -0.0211 0.1779 0.7712
7.750 0.9334 0.01471 0.00759 -0.0192 0.1689 0.7738
8.000 0.9505 0.01507 0.00796 -0.0177 0.1610 0.7766
8.250 0.9660 0.01551 0.00840 -0.0159 0.1538 0.7798
8.500 0.9831 0.01590 0.00880 -0.0144 0.1473 0.7833
8.750 0.9965 0.01644 0.00933 -0.0124 0.1411 0.7870
9.000 1.0145 0.01676 0.00974 -0.0111 0.1358 0.7910
9.250 1.0288 0.01728 0.01027 -0.0094 0.1304 0.7956
9.500 1.0432 0.01784 0.01085 -0.0077 0.1259 0.8006
9.750 1.0599 0.01823 0.01134 -0.0064 0.1214 0.8060
10.000 1.0733 0.01882 0.01196 -0.0047 0.1167 0.8130
10.250 1.0856 0.01947 0.01267 -0.0028 0.1127 0.8212
10.500 1.1023 0.01989 0.01320 -0.0016 0.1091 0.8319
11.000 1.1220 0.02125 0.01480 0.0026 0.1006 0.8835
11.250 1.1620 0.02171 0.01551 -0.0013 0.0967 1.0000
11.500 1.1772 0.02245 0.01626 -0.0004 0.0931 1.0000
11.750 1.1879 0.02348 0.01725 0.0010 0.0889 1.0000
12.000 1.2038 0.02419 0.01803 0.0018 0.0857 1.0000
12.250 1.2189 0.02496 0.01885 0.0026 0.0825 1.0000
12.500 1.2313 0.02592 0.01981 0.0036 0.0792 1.0000
12.750 1.2416 0.02705 0.02094 0.0048 0.0753 1.0000
13.000 1.2569 0.02785 0.02182 0.0055 0.0727 1.0000
13.250 1.2699 0.02882 0.02282 0.0063 0.0695 1.0000
13.500 1.2782 0.03016 0.02416 0.0073 0.0662 1.0000
13.750 1.2889 0.03135 0.02542 0.0082 0.0640 1.0000
14.000 1.3028 0.03231 0.02645 0.0088 0.0614 1.0000
14.250 1.3135 0.03353 0.02769 0.0095 0.0585 1.0000
14.500 1.3195 0.03517 0.02934 0.0104 0.0560 1.0000
14.750 1.3301 0.03646 0.03072 0.0109 0.0538 1.0000
15.000 1.3416 0.03769 0.03203 0.0114 0.0515 1.0000
15.250 1.3496 0.03924 0.03363 0.0120 0.0493 1.0000
15.500 1.3539 0.04117 0.03558 0.0126 0.0471 1.0000
15.750 1.3612 0.04287 0.03736 0.0130 0.0452 1.0000
16.000 1.3705 0.04440 0.03899 0.0133 0.0433 1.0000
16.250 1.3769 0.04626 0.04090 0.0136 0.0416 1.0000
16.500 1.3795 0.04852 0.04320 0.0138 0.0396 1.0000
16.750 1.3828 0.05079 0.04555 0.0140 0.0377 1.0000
17.000 1.3895 0.05276 0.04763 0.0140 0.0358 1.0000
17.250 1.3922 0.05520 0.05013 0.0139 0.0340 1.0000
17.500 1.3896 0.05831 0.05329 0.0136 0.0317 1.0000
17.750 1.3938 0.06070 0.05579 0.0133 0.0295 1.0000
18.000 1.3917 0.06394 0.05910 0.0128 0.0272 1.0000
18.250 1.3864 0.06770 0.06294 0.0120 0.0246 1.0000
18.500 1.3802 0.07168 0.06700 0.0109 0.0224 1.0000
18.750 1.3681 0.07669 0.07209 0.0094 0.0199 1.0000
19.000 1.3560 0.08191 0.07742 0.0075 0.0181 1.0000
19.250 1.3397 0.08800 0.08363 0.0050 0.0172 1.0000
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Polar data table (+)
Polar graphs
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