NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 200,000 Max Cl/Cd: 56.05 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0115-il-200000-n5.txt Download as CSV file: xf-nlf0115-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4629 0.08687 0.08315 -0.0582 1.0000 0.0190
-11.000 -0.4992 0.07603 0.07226 -0.0643 1.0000 0.0185
-10.750 -0.5386 0.06872 0.06484 -0.0660 1.0000 0.0181
-10.500 -0.5611 0.06536 0.06144 -0.0649 1.0000 0.0183
-10.000 -0.6276 0.05328 0.04879 -0.0641 0.9924 0.0175
-9.750 -0.6182 0.05133 0.04672 -0.0654 0.9857 0.0179
-9.500 -0.6141 0.04778 0.04291 -0.0659 0.9774 0.0183
-9.250 -0.6067 0.04376 0.03855 -0.0664 0.9705 0.0183
-9.000 -0.6002 0.03968 0.03404 -0.0657 0.9619 0.0182
-8.750 -0.5899 0.03614 0.03008 -0.0647 0.9530 0.0181
-8.250 -0.5541 0.03090 0.02412 -0.0637 0.9360 0.0183
-8.000 -0.5304 0.02881 0.02172 -0.0637 0.9282 0.0184
-7.750 -0.5072 0.02708 0.01975 -0.0634 0.9182 0.0186
-7.500 -0.4814 0.02554 0.01799 -0.0633 0.9088 0.0189
-7.250 -0.4501 0.02405 0.01630 -0.0643 0.9018 0.0192
-7.000 -0.4211 0.02279 0.01487 -0.0648 0.8923 0.0197
-6.750 -0.3885 0.02163 0.01356 -0.0659 0.8846 0.0203
-6.500 -0.3583 0.02072 0.01250 -0.0665 0.8748 0.0212
-6.250 -0.3295 0.01976 0.01155 -0.0672 0.8649 0.0221
-5.750 -0.2761 0.01823 0.00990 -0.0674 0.8439 0.0235
-5.500 -0.2529 0.01758 0.00916 -0.0668 0.8332 0.0242
-5.000 -0.2095 0.01652 0.00791 -0.0650 0.8143 0.0259
-4.750 -0.1887 0.01601 0.00734 -0.0640 0.8063 0.0271
-4.500 -0.1676 0.01562 0.00689 -0.0629 0.7982 0.0289
-4.250 -0.1445 0.01530 0.00647 -0.0622 0.7917 0.0319
-4.000 -0.1239 0.01492 0.00609 -0.0611 0.7844 0.0366
-3.750 -0.1020 0.01454 0.00569 -0.0602 0.7782 0.0454
-3.500 -0.0815 0.01411 0.00533 -0.0591 0.7722 0.0707
-3.250 -0.0639 0.01348 0.00498 -0.0577 0.7664 0.1411
-3.000 -0.0667 0.01147 0.00433 -0.0534 0.7612 0.4618
-2.750 -0.0493 0.01169 0.00512 -0.0507 0.7563 0.6438
-2.500 -0.0247 0.01218 0.00561 -0.0493 0.7517 0.6777
-2.250 0.0009 0.01271 0.00614 -0.0480 0.7475 0.7017
-2.000 0.0280 0.01311 0.00650 -0.0472 0.7440 0.7166
-1.750 0.0536 0.01313 0.00643 -0.0468 0.7395 0.7225
-1.500 0.0810 0.01308 0.00631 -0.0468 0.7356 0.7238
-1.250 0.1089 0.01305 0.00619 -0.0470 0.7322 0.7250
-1.000 0.1374 0.01302 0.00606 -0.0473 0.7293 0.7260
-0.750 0.1649 0.01299 0.00597 -0.0474 0.7258 0.7271
-0.500 0.1918 0.01297 0.00591 -0.0474 0.7219 0.7286
-0.250 0.2193 0.01296 0.00585 -0.0475 0.7185 0.7300
0.000 0.2473 0.01295 0.00578 -0.0477 0.7156 0.7313
0.250 0.2760 0.01295 0.00572 -0.0480 0.7129 0.7325
0.500 0.3030 0.01296 0.00570 -0.0481 0.7095 0.7338
0.750 0.3299 0.01298 0.00570 -0.0482 0.7060 0.7351
1.000 0.3573 0.01300 0.00570 -0.0483 0.7026 0.7367
1.250 0.3854 0.01300 0.00566 -0.0485 0.6982 0.7380
1.500 0.4107 0.01297 0.00563 -0.0480 0.6894 0.7391
1.750 0.4367 0.01290 0.00549 -0.0475 0.6777 0.7401
2.000 0.4620 0.01283 0.00538 -0.0469 0.6658 0.7412
2.250 0.4867 0.01281 0.00538 -0.0463 0.6558 0.7425
2.500 0.5140 0.01282 0.00534 -0.0463 0.6490 0.7438
2.750 0.5387 0.01282 0.00540 -0.0458 0.6407 0.7452
3.000 0.5655 0.01283 0.00538 -0.0456 0.6329 0.7466
3.250 0.5899 0.01284 0.00545 -0.0450 0.6233 0.7483
3.500 0.6152 0.01286 0.00546 -0.0446 0.6137 0.7501
3.750 0.6401 0.01288 0.00548 -0.0441 0.6027 0.7520
4.000 0.6639 0.01291 0.00555 -0.0434 0.5899 0.7537
4.250 0.6870 0.01293 0.00560 -0.0425 0.5740 0.7551
4.500 0.7094 0.01296 0.00564 -0.0415 0.5536 0.7566
4.750 0.7300 0.01303 0.00569 -0.0401 0.5211 0.7583
5.000 0.7443 0.01328 0.00567 -0.0375 0.4642 0.7603
5.250 0.7518 0.01385 0.00588 -0.0338 0.4014 0.7625
5.500 0.7604 0.01447 0.00624 -0.0305 0.3523 0.7649
5.750 0.7711 0.01503 0.00662 -0.0277 0.3152 0.7673
6.000 0.7821 0.01552 0.00699 -0.0249 0.2874 0.7696
6.250 0.7932 0.01598 0.00738 -0.0221 0.2645 0.7719
6.500 0.8057 0.01646 0.00780 -0.0197 0.2452 0.7747
6.750 0.8195 0.01695 0.00824 -0.0176 0.2289 0.7778
7.000 0.8341 0.01745 0.00871 -0.0157 0.2155 0.7811
7.250 0.8496 0.01793 0.00918 -0.0140 0.2033 0.7846
7.500 0.8651 0.01840 0.00967 -0.0123 0.1927 0.7875
7.750 0.8794 0.01892 0.01019 -0.0104 0.1831 0.7910
8.000 0.8946 0.01942 0.01072 -0.0088 0.1745 0.7950
8.250 0.9097 0.01995 0.01128 -0.0072 0.1674 0.7994
8.500 0.9246 0.02048 0.01185 -0.0056 0.1601 0.8038
8.750 0.9389 0.02106 0.01247 -0.0040 0.1537 0.8091
9.000 0.9550 0.02162 0.01310 -0.0027 0.1472 0.8152
9.250 0.9684 0.02232 0.01381 -0.0012 0.1419 0.8218
9.500 0.9853 0.02287 0.01447 -0.0001 0.1364 0.8301
9.750 1.0000 0.02351 0.01519 0.0012 0.1311 0.8406
10.000 1.0134 0.02425 0.01599 0.0026 0.1266 0.8549
10.250 1.0306 0.02483 0.01675 0.0034 0.1220 0.8776
10.500 1.0554 0.02559 0.01768 0.0023 0.1166 0.9303
10.750 1.0685 0.02643 0.01853 0.0033 0.1126 1.0000
11.000 1.0844 0.02720 0.01940 0.0041 0.1085 1.0000
11.250 1.0983 0.02810 0.02034 0.0050 0.1047 1.0000
11.500 1.1097 0.02919 0.02141 0.0060 0.1012 1.0000
11.750 1.1243 0.03009 0.02240 0.0068 0.0977 1.0000
12.000 1.1381 0.03105 0.02345 0.0076 0.0940 1.0000
12.250 1.1498 0.03215 0.02458 0.0085 0.0907 1.0000
12.500 1.1593 0.03345 0.02588 0.0095 0.0878 1.0000
12.750 1.1731 0.03447 0.02704 0.0101 0.0849 1.0000
13.000 1.1851 0.03563 0.02829 0.0109 0.0818 1.0000
13.250 1.1952 0.03693 0.02965 0.0116 0.0791 1.0000
13.500 1.2026 0.03847 0.03120 0.0124 0.0765 1.0000
13.750 1.2135 0.03979 0.03265 0.0130 0.0741 1.0000
14.000 1.2237 0.04118 0.03417 0.0136 0.0713 1.0000
14.250 1.2321 0.04274 0.03582 0.0142 0.0690 1.0000
14.500 1.2383 0.04449 0.03762 0.0147 0.0668 1.0000
14.750 1.2436 0.04638 0.03956 0.0151 0.0644 1.0000
15.000 1.2518 0.04807 0.04142 0.0154 0.0618 1.0000
15.250 1.2578 0.05000 0.04346 0.0157 0.0593 1.0000
15.500 1.2607 0.05224 0.04575 0.0157 0.0566 1.0000
15.750 1.2630 0.05464 0.04822 0.0158 0.0544 1.0000
16.000 1.2684 0.05680 0.05056 0.0157 0.0515 1.0000
16.250 1.2706 0.05936 0.05322 0.0154 0.0489 1.0000
16.500 1.2698 0.06234 0.05628 0.0150 0.0472 1.0000
16.750 1.2691 0.06540 0.05944 0.0144 0.0453 1.0000
17.000 1.2696 0.06842 0.06263 0.0138 0.0433 1.0000
17.250 1.2676 0.07185 0.06620 0.0129 0.0417 1.0000
17.500 1.2631 0.07576 0.07022 0.0117 0.0402 1.0000
17.750 1.2557 0.08021 0.07478 0.0101 0.0389 1.0000
18.000 1.2484 0.08481 0.07950 0.0083 0.0379 1.0000
18.250 1.2417 0.08948 0.08436 0.0064 0.0366 1.0000
18.500 1.2324 0.09472 0.08976 0.0040 0.0355 1.0000
18.750 1.2208 0.10054 0.09575 0.0012 0.0344 1.0000
19.000 1.2063 0.10703 0.10239 -0.0022 0.0335 1.0000
19.250 1.1898 0.11405 0.10954 -0.0059 0.0328 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NLF(1)-0115 (nlf0115-il)