NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 100,000 Max Cl/Cd: 27.1 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s810-nr-100000-n5.txt Download as CSV file: xf-s810-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S810 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4353 0.09798 0.09311 -0.0779 0.8883 0.0494
-12.000 -0.4488 0.09289 0.08792 -0.0806 0.8802 0.0493
-11.750 -0.4656 0.08813 0.08303 -0.0826 0.8733 0.0493
-11.500 -0.4849 0.08383 0.07859 -0.0838 0.8670 0.0496
-11.250 -0.5066 0.08009 0.07468 -0.0842 0.8611 0.0502
-11.000 -0.5219 0.07692 0.07134 -0.0839 0.8563 0.0503
-10.750 -0.5511 0.07530 0.06948 -0.0822 0.8503 0.0516
-10.500 -0.5858 0.07544 0.06932 -0.0781 0.8445 0.0525
-10.250 -0.6110 0.07542 0.06902 -0.0739 0.8399 0.0528
-10.000 -0.6287 0.07511 0.06838 -0.0700 0.8356 0.0531
-9.750 -0.5983 0.06391 0.05748 -0.0742 0.8343 0.0560
-8.750 -0.5620 0.05260 0.04479 -0.0655 0.8228 0.0272
-8.500 -0.5498 0.04922 0.04120 -0.0646 0.8206 0.0258
-8.250 -0.5364 0.04660 0.03833 -0.0633 0.8185 0.0247
-8.000 -0.5197 0.04401 0.03543 -0.0621 0.8166 0.0236
-7.750 -0.4986 0.04164 0.03274 -0.0612 0.8151 0.0226
-7.500 -0.4731 0.03936 0.03016 -0.0608 0.8133 0.0220
-7.250 -0.4434 0.03729 0.02781 -0.0610 0.8117 0.0217
-7.000 -0.4135 0.03561 0.02596 -0.0615 0.8101 0.0230
-6.750 -0.3801 0.03413 0.02426 -0.0624 0.8086 0.0250
-6.500 -0.3173 0.03201 0.02195 -0.0665 0.8081 0.0257
-6.250 -0.2578 0.03094 0.02078 -0.0689 0.8077 0.0262
-6.000 -0.2146 0.03051 0.02032 -0.0693 0.8065 0.0268
-5.750 -0.1819 0.03043 0.02021 -0.0685 0.8052 0.0279
-5.500 -0.1596 0.03031 0.02009 -0.0670 0.8036 0.0291
-5.250 -0.1489 0.02971 0.01946 -0.0650 0.8020 0.0321
-5.000 -0.1383 0.02905 0.01872 -0.0634 0.8006 0.0348
-4.750 -0.1289 0.02841 0.01798 -0.0618 0.7986 0.0372
-4.500 -0.1200 0.02777 0.01722 -0.0600 0.7966 0.0394
-4.250 -0.1135 0.02707 0.01644 -0.0579 0.7946 0.0425
-4.000 -0.1071 0.02645 0.01575 -0.0558 0.7925 0.0493
-3.750 -0.1050 0.02578 0.01505 -0.0529 0.7902 0.0627
-3.500 -0.1188 0.02477 0.01425 -0.0480 0.7879 0.1156
-3.250 -0.1434 0.02336 0.01333 -0.0421 0.7853 0.2650
-3.000 -0.1609 0.02364 0.01517 -0.0342 0.7822 0.5779
-2.750 -0.1469 0.02566 0.01709 -0.0308 0.7797 0.6345
-2.500 -0.0981 0.02953 0.02095 -0.0293 0.7790 0.6611
-2.250 -0.0498 0.03167 0.02301 -0.0297 0.7783 0.6712
-2.000 -0.0533 0.03077 0.02198 -0.0270 0.7760 0.6778
-1.750 -0.0306 0.03074 0.02186 -0.0266 0.7746 0.6791
-1.500 -0.0079 0.03063 0.02166 -0.0264 0.7732 0.6805
-1.250 0.0052 0.03069 0.02167 -0.0248 0.7707 0.6824
-1.000 0.0097 0.03084 0.02181 -0.0222 0.7672 0.6855
-0.750 0.0167 0.03049 0.02136 -0.0205 0.7640 0.6900
-0.500 0.0336 0.03028 0.02108 -0.0199 0.7619 0.6923
-0.250 0.0571 0.03028 0.02104 -0.0197 0.7603 0.6935
0.000 0.0826 0.03026 0.02098 -0.0199 0.7590 0.6949
0.250 0.0810 0.03082 0.02157 -0.0162 0.7538 0.6973
0.500 0.0927 0.03098 0.02171 -0.0146 0.7501 0.6997
0.750 0.1137 0.03089 0.02159 -0.0145 0.7477 0.7020
1.000 0.1394 0.03067 0.02130 -0.0154 0.7459 0.7046
1.250 0.1678 0.03056 0.02118 -0.0162 0.7446 0.7064
1.500 0.1571 0.03143 0.02212 -0.0111 0.7365 0.7082
1.750 0.1803 0.03156 0.02226 -0.0110 0.7339 0.7098
2.000 0.2083 0.03156 0.02228 -0.0116 0.7319 0.7114
2.250 0.2392 0.03149 0.02225 -0.0127 0.7305 0.7130
2.500 0.2277 0.03226 0.02303 -0.0080 0.7210 0.7156
2.750 0.2576 0.03221 0.02300 -0.0091 0.7187 0.7176
3.000 0.2915 0.03209 0.02291 -0.0109 0.7170 0.7199
3.500 0.3134 0.03291 0.02389 -0.0070 0.7048 0.7230
3.750 0.3471 0.03281 0.02388 -0.0082 0.7029 0.7244
4.250 0.3787 0.03340 0.02462 -0.0062 0.6902 0.7280
4.500 0.4156 0.03313 0.02448 -0.0078 0.6883 0.7298
5.000 0.4552 0.03345 0.02498 -0.0069 0.6750 0.7343
5.500 0.4989 0.03345 0.02526 -0.0056 0.6613 0.7374
6.000 0.5515 0.03275 0.02490 -0.0052 0.6465 0.7408
6.250 0.5649 0.03285 0.02513 -0.0036 0.6342 0.7429
6.750 0.6024 0.03243 0.02498 -0.0017 0.6081 0.7478
7.000 0.6209 0.03204 0.02481 -0.0002 0.5931 0.7496
7.250 0.6294 0.03231 0.02524 0.0019 0.5728 0.7515
7.500 0.6480 0.03193 0.02503 0.0032 0.5519 0.7535
7.750 0.6719 0.03123 0.02446 0.0042 0.5239 0.7556
8.000 0.7359 0.02716 0.02004 0.0039 0.4311 0.7576
8.250 0.7460 0.02761 0.01986 0.0064 0.3345 0.7598
8.500 0.7467 0.02906 0.02089 0.0088 0.2663 0.7622
8.750 0.7489 0.03047 0.02198 0.0111 0.2071 0.7641
9.000 0.7560 0.03172 0.02300 0.0127 0.1620 0.7663
9.250 0.7650 0.03294 0.02406 0.0141 0.1292 0.7687
9.500 0.7751 0.03417 0.02519 0.0152 0.1047 0.7713
9.750 0.7860 0.03543 0.02638 0.0161 0.0881 0.7739
10.000 0.7968 0.03674 0.02765 0.0170 0.0766 0.7763
10.250 0.8082 0.03793 0.02899 0.0181 0.0686 0.7782
10.500 0.8184 0.03931 0.03045 0.0192 0.0623 0.7804
10.750 0.8305 0.04058 0.03183 0.0199 0.0549 0.7829
11.000 0.8423 0.04197 0.03331 0.0206 0.0479 0.7857
11.250 0.8523 0.04347 0.03480 0.0209 0.0404 0.7887
11.500 0.8646 0.04480 0.03631 0.0215 0.0340 0.7915
11.750 0.8727 0.04652 0.03812 0.0223 0.0288 0.7942
12.000 0.8833 0.04823 0.04001 0.0230 0.0248 0.7972
12.250 0.8912 0.05023 0.04210 0.0236 0.0222 0.8004
12.500 0.9020 0.05250 0.04449 0.0243 0.0204 0.8034
12.750 0.9150 0.05460 0.04689 0.0250 0.0189 0.8061
13.000 0.9249 0.05693 0.04950 0.0256 0.0178 0.8090
13.250 0.9309 0.05940 0.05225 0.0261 0.0168 0.8124
13.500 0.9336 0.06189 0.05491 0.0262 0.0159 0.8160
13.750 0.9330 0.06456 0.05770 0.0262 0.0149 0.8195
14.000 0.9315 0.06782 0.06113 0.0264 0.0144 0.8230
14.250 0.9262 0.07168 0.06538 0.0264 0.0139 0.8268
14.500 0.9196 0.07583 0.06984 0.0259 0.0137 0.8309
14.750 0.9082 0.08062 0.07496 0.0253 0.0134 0.8345
15.000 0.8945 0.08586 0.08050 0.0240 0.0134 0.8384
15.250 0.8791 0.09172 0.08663 0.0220 0.0133 0.8426
15.500 0.8628 0.09806 0.09323 0.0192 0.0134 0.8469
15.750 0.8426 0.10552 0.10095 0.0156 0.0134 0.8509
16.000 0.8225 0.11367 0.10931 0.0110 0.0135 0.8554
16.500 0.7803 0.13301 0.12898 -0.0006 0.0140 0.8640
16.750 0.7653 0.14199 0.13803 -0.0058 0.0144 0.8696
|
Polar data table (+)
Polar graphs
<< Back to NREL's S810 Airfoil (s810-nr)