NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 100,000 Max Cl/Cd: 45.46 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0115-il-100000.txt Download as CSV file: xf-nlf0115-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3139 0.11748 0.11275 -0.0464 1.0000 0.1152
-11.500 -0.2970 0.11503 0.11031 -0.0442 1.0000 0.1187
-11.250 -0.4318 0.11420 0.10915 -0.0504 1.0000 0.1144
-11.000 -0.3979 0.11196 0.10687 -0.0454 1.0000 0.1182
-10.750 -0.3964 0.10903 0.10398 -0.0452 1.0000 0.1224
-10.500 -0.4305 0.10465 0.09974 -0.0498 1.0000 0.1277
-10.250 -0.4846 0.09923 0.09444 -0.0555 1.0000 0.1285
-10.000 -0.4172 0.09822 0.09339 -0.0467 1.0000 0.1341
-9.750 -0.4247 0.09503 0.09027 -0.0468 1.0000 0.1393
-9.500 -0.4782 0.08943 0.08482 -0.0511 1.0000 0.1427
-9.250 -0.5238 0.08633 0.08180 -0.0503 1.0000 0.1431
-9.000 -0.5621 0.08462 0.08017 -0.0463 1.0000 0.1431
-8.750 -0.6016 0.08357 0.07920 -0.0407 1.0000 0.1432
-8.500 -0.6379 0.08264 0.07830 -0.0354 1.0000 0.1433
-8.250 -0.6782 0.08196 0.07757 -0.0300 1.0000 0.1436
-7.750 -0.6612 0.07519 0.07105 -0.0261 0.9998 0.1523
-6.000 -0.5529 0.04224 0.03471 -0.0362 0.9469 0.0792
-5.750 -0.5321 0.03997 0.03154 -0.0341 0.9405 0.0718
-5.500 -0.5041 0.03813 0.02942 -0.0343 0.9351 0.0707
-5.250 -0.4694 0.03533 0.02641 -0.0357 0.9319 0.0691
-5.000 -0.4445 0.03365 0.02452 -0.0352 0.9268 0.0681
-4.750 -0.4181 0.03226 0.02294 -0.0349 0.9220 0.0679
-4.500 -0.3841 0.03094 0.02145 -0.0357 0.9187 0.0685
-4.250 -0.3458 0.02988 0.02025 -0.0374 0.9162 0.0703
-4.000 -0.3314 0.02900 0.01944 -0.0352 0.9101 0.0731
-3.750 -0.3056 0.02821 0.01877 -0.0351 0.9056 0.0787
-3.500 -0.2752 0.02752 0.01805 -0.0355 0.9025 0.0841
-3.250 -0.2644 0.02690 0.01755 -0.0329 0.8977 0.0913
-3.000 -0.2508 0.02643 0.01710 -0.0307 0.8925 0.1030
-2.750 -0.2448 0.02377 0.01591 -0.0284 0.8884 0.3370
-2.500 -0.2597 0.02562 0.01924 -0.0156 0.8833 0.7310
-2.250 -0.0485 0.03316 0.02659 -0.0268 0.8935 0.8921
-2.000 -0.0282 0.03293 0.02623 -0.0267 0.8892 0.8961
-1.750 0.0158 0.03263 0.02576 -0.0308 0.8870 0.8987
-1.500 0.0054 0.03277 0.02587 -0.0253 0.8791 0.9024
-1.250 0.0174 0.03267 0.02569 -0.0237 0.8744 0.9054
-1.000 0.0399 0.03249 0.02541 -0.0238 0.8712 0.9078
-0.750 -0.0034 0.03264 0.02559 -0.0126 0.8622 0.9118
-0.500 0.0223 0.03256 0.02542 -0.0134 0.8584 0.9134
-0.250 0.0609 0.03247 0.02523 -0.0163 0.8557 0.9148
0.000 0.0163 0.03258 0.02537 -0.0051 0.8471 0.9192
0.250 0.0190 0.03240 0.02514 -0.0016 0.8423 0.9224
0.500 0.0054 0.03223 0.02495 0.0045 0.8368 0.9261
0.750 0.0189 0.03236 0.02504 0.0056 0.8308 0.9284
1.000 0.0510 0.03239 0.02500 0.0040 0.8263 0.9296
1.250 0.0654 0.03253 0.02512 0.0051 0.8204 0.9320
1.500 0.0768 0.03263 0.02520 0.0067 0.8136 0.9356
1.750 0.1192 0.03264 0.02516 0.0037 0.8089 0.9366
2.000 0.1096 0.03276 0.02528 0.0086 0.7997 0.9412
2.250 0.1570 0.03276 0.02526 0.0049 0.7938 0.9419
2.500 0.1802 0.03300 0.02550 0.0046 0.7833 0.9444
2.750 0.2479 0.03242 0.02491 -0.0012 0.7766 0.9441
3.000 0.2707 0.03243 0.02494 -0.0011 0.7639 0.9472
3.250 0.3050 0.03218 0.02471 -0.0022 0.7528 0.9493
3.500 0.3740 0.03103 0.02359 -0.0077 0.7462 0.9486
3.750 0.3933 0.03098 0.02358 -0.0067 0.7341 0.9524
4.000 0.4843 0.02906 0.02173 -0.0151 0.7303 0.9495
4.250 0.5028 0.02885 0.02158 -0.0136 0.7183 0.9536
4.500 0.6091 0.02638 0.01920 -0.0243 0.7138 0.9493
4.750 0.6330 0.02591 0.01879 -0.0233 0.7011 0.9531
5.000 0.6726 0.02493 0.01789 -0.0243 0.6892 0.9557
5.250 0.7294 0.02363 0.01667 -0.0281 0.6761 0.9564
5.500 0.7755 0.02261 0.01573 -0.0305 0.6587 0.9581
5.750 0.8162 0.02161 0.01482 -0.0319 0.6379 0.9603
6.000 0.8471 0.02078 0.01404 -0.0317 0.6127 0.9639
6.250 0.8624 0.02017 0.01350 -0.0290 0.5803 0.9700
6.500 0.8842 0.01964 0.01295 -0.0276 0.5167 0.9755
6.750 0.8982 0.01976 0.01238 -0.0249 0.4260 0.9828
7.000 0.9147 0.02092 0.01292 -0.0239 0.3626 0.9901
7.250 0.9368 0.02209 0.01367 -0.0242 0.3243 0.9982
7.500 0.9335 0.02254 0.01399 -0.0196 0.3072 1.0000
7.750 0.9154 0.02256 0.01398 -0.0123 0.2977 1.0000
8.000 0.9256 0.02321 0.01446 -0.0101 0.2814 1.0000
8.250 0.9460 0.02409 0.01518 -0.0098 0.2650 1.0000
8.500 0.9687 0.02501 0.01601 -0.0098 0.2502 1.0000
8.750 0.9937 0.02600 0.01697 -0.0101 0.2373 1.0000
9.000 1.0197 0.02706 0.01798 -0.0107 0.2256 1.0000
9.250 1.0491 0.02823 0.01902 -0.0117 0.2145 1.0000
9.500 1.0699 0.02920 0.02007 -0.0113 0.2051 1.0000
9.750 1.0956 0.03043 0.02133 -0.0117 0.1964 1.0000
10.000 1.1203 0.03152 0.02238 -0.0119 0.1878 1.0000
10.250 1.1407 0.03284 0.02385 -0.0114 0.1805 1.0000
10.500 1.1634 0.03398 0.02499 -0.0112 0.1733 1.0000
10.750 1.1827 0.03545 0.02661 -0.0106 0.1668 1.0000
11.000 1.1981 0.03665 0.02795 -0.0094 0.1606 1.0000
11.250 1.2246 0.03838 0.02965 -0.0101 0.1546 1.0000
11.500 1.2306 0.03975 0.03133 -0.0074 0.1497 1.0000
11.750 1.2469 0.04098 0.03261 -0.0064 0.1444 1.0000
12.000 1.2643 0.04303 0.03479 -0.0059 0.1398 1.0000
12.250 1.2613 0.04467 0.03675 -0.0021 0.1363 1.0000
12.500 1.2692 0.04617 0.03839 -0.0002 0.1322 1.0000
12.750 1.2984 0.04835 0.04047 -0.0015 0.1271 1.0000
13.000 1.2817 0.05030 0.04281 0.0034 0.1254 1.0000
13.250 1.2671 0.05269 0.04553 0.0074 0.1233 1.0000
13.500 1.2555 0.05521 0.04832 0.0105 0.1210 1.0000
13.750 1.2568 0.05727 0.05051 0.0122 0.1181 1.0000
14.000 1.2879 0.05932 0.05243 0.0110 0.1135 1.0000
14.250 1.2594 0.06254 0.05598 0.0146 0.1129 1.0000
14.500 1.2290 0.06648 0.06024 0.0172 0.1124 1.0000
14.750 1.1952 0.07127 0.06532 0.0188 0.1121 1.0000
15.000 1.1571 0.07709 0.07138 0.0192 0.1121 1.0000
15.250 1.1134 0.08433 0.07885 0.0182 0.1124 1.0000
15.500 1.0666 0.09324 0.08794 0.0155 0.1130 1.0000
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Polar data table (+)
Polar graphs
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