LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 500,000 Max Cl/Cd: 51.17 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-500000-n5.txt Download as CSV file: xf-lwk80120k25-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-120/K25
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9561 0.11919 0.11649 -0.0015 1.0000 0.0086
-17.000 -1.0325 0.09856 0.09554 -0.0125 1.0000 0.0081
-16.750 -1.0678 0.08687 0.08363 -0.0192 1.0000 0.0080
-16.500 -1.0939 0.07733 0.07391 -0.0250 1.0000 0.0080
-16.250 -1.1173 0.06900 0.06539 -0.0300 1.0000 0.0080
-16.000 -1.1353 0.06227 0.05846 -0.0336 1.0000 0.0080
-15.750 -1.1376 0.05842 0.05451 -0.0356 1.0000 0.0082
-15.500 -1.1543 0.05303 0.04891 -0.0375 1.0000 0.0081
-15.250 -1.1528 0.05025 0.04605 -0.0383 1.0000 0.0084
-15.000 -1.1588 0.04677 0.04243 -0.0389 1.0000 0.0085
-14.750 -1.1625 0.04371 0.03922 -0.0390 1.0000 0.0085
-14.500 -1.1613 0.04133 0.03671 -0.0389 1.0000 0.0087
-14.250 -1.1629 0.03873 0.03397 -0.0384 1.0000 0.0088
-14.000 -1.1596 0.03670 0.03180 -0.0378 1.0000 0.0090
-13.750 -1.1563 0.03473 0.02969 -0.0369 1.0000 0.0090
-13.500 -1.1503 0.03303 0.02786 -0.0360 1.0000 0.0093
-13.250 -1.1442 0.03138 0.02608 -0.0350 1.0000 0.0095
-13.000 -1.1365 0.02991 0.02449 -0.0338 1.0000 0.0095
-12.750 -1.1268 0.02863 0.02309 -0.0327 1.0000 0.0097
-12.500 -1.1171 0.02735 0.02169 -0.0315 1.0000 0.0101
-12.250 -1.1087 0.02601 0.02026 -0.0300 1.0000 0.0103
-12.000 -1.0971 0.02497 0.01916 -0.0287 1.0000 0.0108
-11.750 -1.0843 0.02404 0.01816 -0.0274 1.0000 0.0111
-11.500 -1.0709 0.02317 0.01720 -0.0260 1.0000 0.0114
-11.250 -1.0575 0.02233 0.01629 -0.0245 1.0000 0.0118
-11.000 -1.0436 0.02157 0.01546 -0.0228 1.0000 0.0122
-10.750 -1.0295 0.02087 0.01468 -0.0211 1.0000 0.0127
-10.250 -0.9521 0.01884 0.01245 -0.0283 0.9407 0.0143
-10.000 -0.9131 0.01806 0.01157 -0.0317 0.9276 0.0154
-9.750 -0.8819 0.01742 0.01082 -0.0333 0.9135 0.0164
-9.500 -0.8579 0.01692 0.01019 -0.0333 0.9011 0.0173
-9.250 -0.8385 0.01643 0.00965 -0.0322 0.8908 0.0191
-8.750 -0.7998 0.01567 0.00873 -0.0298 0.8754 0.0219
-8.500 -0.7801 0.01526 0.00826 -0.0286 0.8694 0.0236
-8.250 -0.7603 0.01486 0.00784 -0.0274 0.8644 0.0256
-8.000 -0.7397 0.01452 0.00745 -0.0263 0.8595 0.0276
-7.750 -0.7186 0.01421 0.00706 -0.0252 0.8551 0.0298
-7.500 -0.6978 0.01386 0.00671 -0.0242 0.8511 0.0336
-7.250 -0.6759 0.01358 0.00640 -0.0232 0.8468 0.0365
-7.000 -0.6546 0.01324 0.00605 -0.0222 0.8429 0.0403
-6.750 -0.6325 0.01296 0.00575 -0.0213 0.8395 0.0445
-6.500 -0.6097 0.01271 0.00544 -0.0205 0.8366 0.0483
-6.250 -0.5876 0.01240 0.00517 -0.0196 0.8333 0.0541
-6.000 -0.5644 0.01216 0.00490 -0.0189 0.8299 0.0589
-5.750 -0.5418 0.01188 0.00464 -0.0180 0.8266 0.0669
-5.500 -0.5185 0.01164 0.00439 -0.0173 0.8237 0.0740
-5.250 -0.4950 0.01141 0.00416 -0.0166 0.8211 0.0831
-5.000 -0.4718 0.01114 0.00394 -0.0159 0.8182 0.0950
-4.750 -0.4486 0.01087 0.00373 -0.0151 0.8152 0.1102
-4.500 -0.4259 0.01057 0.00350 -0.0143 0.8122 0.1318
-4.250 -0.4030 0.01028 0.00329 -0.0135 0.8095 0.1570
-4.000 -0.3806 0.00995 0.00309 -0.0126 0.8071 0.1908
-3.750 -0.3593 0.00955 0.00288 -0.0116 0.8045 0.2396
-3.500 -0.3381 0.00914 0.00268 -0.0105 0.8016 0.2925
-3.250 -0.3179 0.00868 0.00248 -0.0093 0.7985 0.3558
-3.000 -0.2993 0.00816 0.00226 -0.0077 0.7957 0.4343
-2.750 -0.2818 0.00762 0.00205 -0.0058 0.7932 0.5218
-2.500 -0.2628 0.00725 0.00198 -0.0040 0.7909 0.6005
-2.250 -0.2396 0.00710 0.00200 -0.0030 0.7880 0.6461
-2.000 -0.2141 0.00705 0.00201 -0.0024 0.7853 0.6720
-1.750 -0.1878 0.00703 0.00201 -0.0020 0.7826 0.6894
-1.500 -0.1615 0.00703 0.00203 -0.0016 0.7801 0.7059
-1.250 -0.1349 0.00705 0.00206 -0.0013 0.7777 0.7205
-1.000 -0.1081 0.00709 0.00208 -0.0010 0.7755 0.7325
-0.750 -0.0813 0.00711 0.00213 -0.0007 0.7724 0.7418
-0.500 -0.0543 0.00712 0.00217 -0.0004 0.7692 0.7495
-0.250 -0.0273 0.00715 0.00220 -0.0002 0.7659 0.7568
0.000 0.0000 0.00716 0.00218 0.0000 0.7622 0.7622
0.250 0.0273 0.00715 0.00220 0.0002 0.7567 0.7659
0.500 0.0543 0.00712 0.00217 0.0004 0.7494 0.7693
0.750 0.0813 0.00711 0.00213 0.0007 0.7418 0.7724
1.000 0.1081 0.00709 0.00209 0.0010 0.7329 0.7754
1.250 0.1349 0.00705 0.00206 0.0013 0.7206 0.7777
1.500 0.1616 0.00703 0.00203 0.0016 0.7064 0.7801
1.750 0.1878 0.00703 0.00201 0.0021 0.6889 0.7826
2.000 0.2139 0.00706 0.00200 0.0025 0.6706 0.7853
2.250 0.2398 0.00710 0.00200 0.0030 0.6481 0.7880
2.500 0.2626 0.00725 0.00198 0.0041 0.5987 0.7909
2.750 0.2815 0.00764 0.00206 0.0059 0.5195 0.7933
3.000 0.2995 0.00815 0.00226 0.0077 0.4365 0.7957
3.250 0.3176 0.00870 0.00248 0.0093 0.3531 0.7985
3.500 0.3380 0.00915 0.00269 0.0106 0.2911 0.8015
3.750 0.3595 0.00953 0.00288 0.0116 0.2416 0.8045
4.000 0.3808 0.00994 0.00309 0.0126 0.1929 0.8071
4.250 0.4031 0.01027 0.00329 0.0135 0.1576 0.8095
4.500 0.4258 0.01058 0.00351 0.0143 0.1306 0.8123
4.750 0.4486 0.01087 0.00373 0.0151 0.1106 0.8152
5.000 0.4718 0.01114 0.00394 0.0159 0.0949 0.8182
5.250 0.4950 0.01141 0.00416 0.0166 0.0828 0.8211
5.500 0.5185 0.01164 0.00439 0.0173 0.0739 0.8237
5.750 0.5418 0.01188 0.00464 0.0180 0.0666 0.8265
6.000 0.5645 0.01216 0.00491 0.0189 0.0592 0.8299
6.250 0.5876 0.01240 0.00516 0.0196 0.0537 0.8333
6.500 0.6097 0.01271 0.00545 0.0205 0.0480 0.8366
6.750 0.6326 0.01296 0.00575 0.0213 0.0444 0.8396
7.000 0.6547 0.01324 0.00605 0.0222 0.0404 0.8429
7.250 0.6760 0.01357 0.00639 0.0232 0.0365 0.8470
7.500 0.6978 0.01386 0.00671 0.0242 0.0333 0.8512
7.750 0.7186 0.01421 0.00707 0.0252 0.0298 0.8551
8.000 0.7398 0.01452 0.00745 0.0262 0.0275 0.8595
8.250 0.7604 0.01486 0.00784 0.0273 0.0254 0.8644
8.500 0.7803 0.01526 0.00826 0.0285 0.0235 0.8693
8.750 0.8001 0.01566 0.00873 0.0297 0.0218 0.8753
9.250 0.8389 0.01643 0.00962 0.0321 0.0185 0.8908
9.500 0.8577 0.01697 0.01025 0.0333 0.0175 0.9012
9.750 0.8821 0.01745 0.01084 0.0333 0.0165 0.9134
10.000 0.9136 0.01804 0.01155 0.0317 0.0152 0.9274
10.250 0.9523 0.01885 0.01244 0.0282 0.0140 0.9405
10.500 0.9925 0.01990 0.01359 0.0243 0.0132 0.9561
10.750 1.0304 0.02085 0.01466 0.0210 0.0125 1.0000
11.000 1.0443 0.02158 0.01547 0.0228 0.0121 1.0000
11.250 1.0582 0.02234 0.01630 0.0243 0.0117 1.0000
11.500 1.0723 0.02312 0.01714 0.0258 0.0113 1.0000
11.750 1.0859 0.02397 0.01809 0.0272 0.0111 1.0000
12.000 1.0978 0.02498 0.01917 0.0286 0.0107 1.0000
12.250 1.1083 0.02612 0.02036 0.0300 0.0102 1.0000
12.500 1.1168 0.02747 0.02182 0.0314 0.0099 1.0000
12.750 1.1277 0.02864 0.02311 0.0326 0.0097 1.0000
13.000 1.1347 0.03018 0.02477 0.0339 0.0096 1.0000
13.250 1.1448 0.03145 0.02616 0.0348 0.0093 1.0000
13.500 1.1521 0.03299 0.02782 0.0358 0.0092 1.0000
13.750 1.1575 0.03474 0.02970 0.0367 0.0090 1.0000
14.000 1.1627 0.03654 0.03163 0.0374 0.0088 1.0000
14.250 1.1658 0.03860 0.03382 0.0381 0.0085 1.0000
14.500 1.1662 0.04100 0.03636 0.0385 0.0085 1.0000
14.750 1.1646 0.04369 0.03919 0.0387 0.0084 1.0000
15.000 1.1615 0.04669 0.04233 0.0386 0.0083 1.0000
15.250 1.1590 0.04975 0.04552 0.0381 0.0082 1.0000
15.500 1.1501 0.05382 0.04975 0.0370 0.0082 1.0000
15.750 1.1428 0.05801 0.05407 0.0353 0.0080 1.0000
16.000 1.1279 0.06372 0.05996 0.0326 0.0080 1.0000
16.250 1.1137 0.07000 0.06640 0.0291 0.0080 1.0000
16.500 1.0975 0.07713 0.07370 0.0247 0.0079 1.0000
16.750 1.0648 0.08797 0.08476 0.0182 0.0080 1.0000
17.000 1.0187 0.10192 0.09898 0.0103 0.0083 1.0000
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