LWK 80-150/K25 (lwk80150k25-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-150/K25 (lwk80150k25-il) Reynolds number: 200,000 Max Cl/Cd: 35.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80150k25-il-200000-n5.txt Download as CSV file: xf-lwk80150k25-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-150/K25
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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9169 0.11079 0.10631 -0.0228 1.0000 0.0232
-17.250 -0.9522 0.09938 0.09465 -0.0297 1.0000 0.0230
-17.000 -0.9762 0.09079 0.08583 -0.0349 1.0000 0.0231
-16.750 -0.9989 0.08295 0.07773 -0.0394 1.0000 0.0234
-16.500 -1.0137 0.07696 0.07152 -0.0424 1.0000 0.0235
-16.250 -1.0254 0.07174 0.06609 -0.0446 1.0000 0.0236
-16.000 -1.0348 0.06712 0.06125 -0.0464 1.0000 0.0239
-15.750 -1.0456 0.06258 0.05643 -0.0478 1.0000 0.0242
-15.500 -1.0455 0.05965 0.05346 -0.0484 1.0000 0.0246
-15.250 -1.0450 0.05686 0.05059 -0.0488 1.0000 0.0249
-15.000 -1.0441 0.05416 0.04777 -0.0490 1.0000 0.0250
-14.750 -1.0417 0.05179 0.04531 -0.0491 1.0000 0.0254
-14.500 -1.0388 0.04947 0.04288 -0.0490 1.0000 0.0258
-14.250 -1.0350 0.04727 0.04055 -0.0487 1.0000 0.0263
-14.000 -1.0297 0.04521 0.03837 -0.0484 1.0000 0.0267
-13.750 -1.0231 0.04329 0.03632 -0.0479 1.0000 0.0272
-13.500 -1.0157 0.04148 0.03435 -0.0474 1.0000 0.0280
-13.250 -1.0064 0.03981 0.03252 -0.0468 1.0000 0.0285
-13.000 -0.9978 0.03822 0.03092 -0.0462 1.0000 0.0293
-12.750 -0.9875 0.03679 0.02945 -0.0456 1.0000 0.0299
-12.500 -0.9763 0.03548 0.02807 -0.0451 1.0000 0.0308
-12.250 -0.9638 0.03422 0.02675 -0.0445 1.0000 0.0315
-12.000 -0.9509 0.03300 0.02542 -0.0438 1.0000 0.0327
-11.750 -0.9334 0.03165 0.02397 -0.0437 0.9785 0.0338
-11.500 -0.9081 0.03032 0.02259 -0.0460 0.9502 0.0350
-11.250 -0.8804 0.02915 0.02132 -0.0482 0.9387 0.0367
-11.000 -0.8539 0.02807 0.02010 -0.0499 0.9291 0.0386
-10.750 -0.8308 0.02701 0.01898 -0.0509 0.9205 0.0407
-10.500 -0.8080 0.02609 0.01798 -0.0517 0.9128 0.0427
-10.250 -0.7868 0.02526 0.01705 -0.0520 0.9062 0.0450
-10.000 -0.7674 0.02440 0.01612 -0.0519 0.9002 0.0471
-9.750 -0.7464 0.02367 0.01535 -0.0520 0.8953 0.0504
-9.500 -0.7261 0.02301 0.01459 -0.0518 0.8905 0.0537
-9.250 -0.7081 0.02223 0.01384 -0.0513 0.8857 0.0570
-9.000 -0.6876 0.02164 0.01316 -0.0509 0.8814 0.0617
-8.750 -0.6696 0.02098 0.01251 -0.0503 0.8773 0.0666
-8.500 -0.6516 0.02045 0.01192 -0.0493 0.8727 0.0717
-8.250 -0.6355 0.01984 0.01134 -0.0481 0.8685 0.0775
-7.750 -0.6020 0.01884 0.01030 -0.0455 0.8618 0.0918
-7.500 -0.5872 0.01835 0.00983 -0.0438 0.8580 0.1005
-7.250 -0.5720 0.01791 0.00939 -0.0421 0.8541 0.1104
-7.000 -0.5582 0.01743 0.00894 -0.0401 0.8503 0.1225
-6.750 -0.5446 0.01698 0.00853 -0.0380 0.8471 0.1364
-6.500 -0.5320 0.01657 0.00818 -0.0356 0.8441 0.1534
-6.250 -0.5211 0.01617 0.00788 -0.0329 0.8405 0.1737
-6.000 -0.5109 0.01576 0.00759 -0.0301 0.8371 0.1998
-5.750 -0.4992 0.01531 0.00727 -0.0275 0.8339 0.2313
-5.500 -0.4881 0.01481 0.00694 -0.0248 0.8309 0.2711
-5.250 -0.4779 0.01429 0.00662 -0.0219 0.8281 0.3190
-5.000 -0.4691 0.01375 0.00636 -0.0188 0.8247 0.3741
-4.750 -0.4607 0.01317 0.00611 -0.0154 0.8214 0.4386
-4.500 -0.4504 0.01267 0.00601 -0.0122 0.8184 0.5148
-4.250 -0.4319 0.01251 0.00618 -0.0101 0.8158 0.5830
-4.000 -0.4081 0.01258 0.00634 -0.0090 0.8137 0.6246
-3.750 -0.3828 0.01270 0.00647 -0.0082 0.8119 0.6495
-3.500 -0.3590 0.01284 0.00660 -0.0073 0.8095 0.6683
-3.250 -0.3349 0.01298 0.00672 -0.0065 0.8066 0.6830
-3.000 -0.3105 0.01310 0.00681 -0.0057 0.8038 0.6958
-2.750 -0.2872 0.01322 0.00688 -0.0047 0.8011 0.7090
-2.500 -0.2593 0.01349 0.00715 -0.0043 0.7990 0.7190
-2.250 -0.2339 0.01363 0.00725 -0.0037 0.7970 0.7283
-2.000 -0.2061 0.01386 0.00745 -0.0033 0.7952 0.7365
-1.750 -0.1818 0.01398 0.00754 -0.0026 0.7928 0.7443
-1.500 -0.1547 0.01421 0.00779 -0.0023 0.7898 0.7491
-1.250 -0.1300 0.01431 0.00788 -0.0017 0.7868 0.7552
-1.000 -0.1059 0.01434 0.00788 -0.0010 0.7839 0.7608
-0.750 -0.0776 0.01442 0.00796 -0.0010 0.7816 0.7637
-0.500 -0.0500 0.01444 0.00798 -0.0008 0.7795 0.7667
-0.250 -0.0230 0.01443 0.00793 -0.0007 0.7776 0.7701
0.000 0.0000 0.01443 0.00793 0.0000 0.7742 0.7741
0.250 0.0230 0.01442 0.00793 0.0007 0.7700 0.7776
0.500 0.0500 0.01444 0.00798 0.0008 0.7667 0.7795
0.750 0.0777 0.01442 0.00796 0.0010 0.7636 0.7816
1.000 0.1059 0.01433 0.00787 0.0010 0.7608 0.7839
1.250 0.1301 0.01431 0.00789 0.0016 0.7553 0.7868
1.500 0.1546 0.01421 0.00780 0.0023 0.7492 0.7898
1.750 0.1818 0.01398 0.00754 0.0026 0.7442 0.7928
2.000 0.2061 0.01386 0.00745 0.0033 0.7363 0.7953
2.250 0.2340 0.01363 0.00725 0.0037 0.7282 0.7971
2.500 0.2593 0.01348 0.00714 0.0044 0.7187 0.7990
2.750 0.2872 0.01322 0.00688 0.0047 0.7090 0.8011
3.000 0.3106 0.01311 0.00681 0.0057 0.6959 0.8037
3.250 0.3348 0.01297 0.00671 0.0065 0.6826 0.8066
3.500 0.3589 0.01283 0.00659 0.0073 0.6677 0.8095
3.750 0.3828 0.01270 0.00646 0.0082 0.6493 0.8119
4.000 0.4080 0.01258 0.00634 0.0090 0.6239 0.8137
4.250 0.4318 0.01251 0.00617 0.0101 0.5812 0.8158
4.500 0.4502 0.01268 0.00601 0.0122 0.5134 0.8184
4.750 0.4604 0.01318 0.00611 0.0155 0.4373 0.8214
5.000 0.4687 0.01376 0.00635 0.0188 0.3722 0.8247
5.250 0.4776 0.01430 0.00663 0.0220 0.3174 0.8282
5.500 0.4881 0.01482 0.00694 0.0248 0.2712 0.8309
5.750 0.4994 0.01530 0.00727 0.0275 0.2318 0.8339
6.000 0.5108 0.01577 0.00759 0.0301 0.1993 0.8371
6.250 0.5213 0.01617 0.00788 0.0329 0.1739 0.8405
6.500 0.5322 0.01657 0.00818 0.0356 0.1538 0.8441
6.750 0.5449 0.01698 0.00853 0.0379 0.1366 0.8471
7.000 0.5584 0.01743 0.00894 0.0401 0.1225 0.8503
7.500 0.5871 0.01836 0.00983 0.0438 0.0997 0.8580
7.750 0.6022 0.01884 0.01030 0.0455 0.0918 0.8617
8.000 0.6182 0.01937 0.01082 0.0469 0.0843 0.8649
8.250 0.6358 0.01984 0.01134 0.0480 0.0777 0.8685
8.500 0.6519 0.02045 0.01192 0.0493 0.0720 0.8727
8.750 0.6700 0.02097 0.01250 0.0502 0.0666 0.8774
9.000 0.6883 0.02162 0.01315 0.0509 0.0616 0.8814
9.250 0.7088 0.02221 0.01382 0.0512 0.0572 0.8857
9.500 0.7271 0.02297 0.01457 0.0516 0.0538 0.8904
9.750 0.7471 0.02365 0.01533 0.0519 0.0505 0.8953
10.000 0.7681 0.02439 0.01612 0.0518 0.0472 0.9001
10.250 0.7875 0.02526 0.01704 0.0518 0.0450 0.9062
10.500 0.8087 0.02610 0.01798 0.0516 0.0425 0.9128
10.750 0.8314 0.02701 0.01896 0.0508 0.0404 0.9204
11.000 0.8546 0.02807 0.02011 0.0497 0.0384 0.9290
11.250 0.8815 0.02911 0.02128 0.0480 0.0365 0.9387
11.500 0.9092 0.03029 0.02255 0.0458 0.0349 0.9503
11.750 0.9341 0.03166 0.02397 0.0436 0.0336 0.9800
12.000 0.9520 0.03299 0.02542 0.0436 0.0327 1.0000
12.250 0.9648 0.03422 0.02674 0.0443 0.0315 1.0000
12.500 0.9770 0.03545 0.02803 0.0449 0.0303 1.0000
12.750 0.9884 0.03678 0.02941 0.0454 0.0297 1.0000
13.000 0.9983 0.03821 0.03088 0.0460 0.0290 1.0000
13.250 1.0076 0.03982 0.03255 0.0466 0.0283 1.0000
13.500 1.0168 0.04149 0.03439 0.0472 0.0277 1.0000
13.750 1.0246 0.04326 0.03630 0.0477 0.0272 1.0000
14.000 1.0310 0.04523 0.03840 0.0482 0.0266 1.0000
14.250 1.0367 0.04722 0.04050 0.0485 0.0262 1.0000
14.500 1.0406 0.04941 0.04281 0.0487 0.0257 1.0000
14.750 1.0437 0.05172 0.04524 0.0488 0.0253 1.0000
15.000 1.0460 0.05413 0.04772 0.0487 0.0249 1.0000
15.250 1.0479 0.05667 0.05033 0.0484 0.0246 1.0000
15.500 1.0482 0.05951 0.05326 0.0481 0.0244 1.0000
15.750 1.0455 0.06284 0.05673 0.0474 0.0241 1.0000
16.000 1.0387 0.06686 0.06097 0.0462 0.0239 1.0000
16.250 1.0263 0.07192 0.06629 0.0442 0.0236 1.0000
16.500 1.0144 0.07720 0.07178 0.0419 0.0234 1.0000
16.750 0.9997 0.08321 0.07801 0.0388 0.0233 1.0000
17.000 0.9802 0.09050 0.08553 0.0346 0.0230 1.0000
17.250 0.9536 0.09955 0.09482 0.0293 0.0231 1.0000
17.500 0.9156 0.11164 0.10719 0.0219 0.0232 1.0000
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