NREL's S827 Airfoil (s827-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S827 Airfoil (s827-nr) Reynolds number: 200,000 Max Cl/Cd: 35.6 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s827-nr-200000.txt Download as CSV file: xf-s827-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S827 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.2002 0.11686 0.11310 -0.1394 0.9456 0.0359
-14.250 -0.2091 0.11112 0.10732 -0.1431 0.9405 0.0360
-14.000 -0.2193 0.10624 0.10238 -0.1458 0.9353 0.0360
-13.750 -0.2184 0.09918 0.09537 -0.1472 0.9328 0.0371
-13.500 -0.2139 0.09549 0.09166 -0.1483 0.9295 0.0377
-13.250 -0.2160 0.09207 0.08823 -0.1488 0.9243 0.0385
-13.000 -0.2291 0.08747 0.08356 -0.1505 0.9199 0.0387
-12.750 -0.2431 0.08312 0.07912 -0.1517 0.9164 0.0390
-12.500 -0.2611 0.07950 0.07543 -0.1516 0.9107 0.0390
-12.250 -0.2783 0.07592 0.07175 -0.1515 0.9063 0.0392
-12.000 -0.2926 0.07267 0.06839 -0.1510 0.9029 0.0398
-11.750 -0.3092 0.06992 0.06555 -0.1498 0.8982 0.0401
-11.500 -0.3245 0.06731 0.06283 -0.1483 0.8940 0.0405
-11.250 -0.3396 0.06474 0.06013 -0.1465 0.8905 0.0414
-11.000 -0.3522 0.06261 0.05787 -0.1444 0.8872 0.0418
-10.750 -0.3675 0.06078 0.05593 -0.1416 0.8827 0.0429
-10.500 -0.3814 0.05912 0.05411 -0.1384 0.8789 0.0441
-10.250 -0.3964 0.05824 0.05301 -0.1341 0.8757 0.0457
-10.000 -0.4268 0.06007 0.05461 -0.1262 0.8705 0.0469
-9.750 -0.4470 0.06156 0.05584 -0.1197 0.8659 0.0475
-9.500 -0.4551 0.06089 0.05495 -0.1154 0.8632 0.0477
-8.750 -0.2509 0.03479 0.02725 -0.1295 0.8661 0.0202
-8.500 -0.1762 0.03375 0.02597 -0.1325 0.8667 0.0208
-8.250 -0.1378 0.03365 0.02583 -0.1327 0.8657 0.0223
-8.000 -0.1120 0.03354 0.02565 -0.1323 0.8643 0.0252
-7.750 -0.0813 0.03382 0.02597 -0.1308 0.8633 0.0292
-7.500 -0.0650 0.03363 0.02577 -0.1293 0.8619 0.0318
-7.250 -0.0569 0.03316 0.02533 -0.1269 0.8605 0.0389
-7.000 -0.0558 0.03315 0.02537 -0.1238 0.8578 0.0482
-6.750 -0.0666 0.03291 0.02522 -0.1193 0.8546 0.0610
-6.500 -0.0795 0.03232 0.02471 -0.1145 0.8514 0.0744
-6.250 -0.0957 0.03156 0.02407 -0.1095 0.8490 0.0917
-6.000 -0.1167 0.03052 0.02314 -0.1040 0.8470 0.1143
-5.750 -0.6865 0.04878 0.04158 -0.0163 0.8927 0.0240
-5.500 -0.6351 0.04617 0.03844 -0.0169 0.8926 0.0193
-5.250 -0.5975 0.04556 0.03770 -0.0179 0.8915 0.0190
-5.000 -0.5185 0.04542 0.03773 -0.0220 0.8927 0.0218
-4.750 -0.5023 0.04526 0.03755 -0.0207 0.8907 0.0239
-4.500 -0.4910 0.04511 0.03735 -0.0184 0.8893 0.0247
-4.250 -0.5286 0.04387 0.03600 -0.0091 0.8826 0.0263
-4.000 -0.5321 0.04270 0.03481 -0.0047 0.8783 0.0270
-3.750 -0.5294 0.04126 0.03333 -0.0026 0.8760 0.0284
-3.500 -0.5140 0.04056 0.03258 -0.0026 0.8748 0.0328
-3.250 -0.5316 0.03890 0.03087 0.0041 0.8669 0.0323
-3.000 -0.5135 0.03768 0.02957 0.0040 0.8639 0.0477
-2.750 -0.4962 0.03442 0.02694 0.0016 0.8624 0.2224
-2.500 -0.4699 0.03521 0.02892 0.0008 0.8611 0.5763
-2.250 -0.4726 0.03514 0.02885 0.0059 0.8539 0.5875
-2.000 -0.4468 0.03709 0.03089 0.0072 0.8502 0.6033
-1.750 -0.3153 0.06390 0.05864 0.0237 0.8508 0.6829
-1.500 -0.3067 0.06224 0.05689 0.0243 0.8482 0.6758
-1.250 -0.3911 0.04189 0.03583 0.0144 0.8385 0.6310
-1.000 -0.3635 0.04311 0.03696 0.0142 0.8356 0.6418
-0.750 -0.3312 0.04386 0.03763 0.0129 0.8337 0.6429
-0.500 -0.2938 0.04435 0.03798 0.0096 0.8326 0.6430
-0.250 -0.3003 0.04315 0.03674 0.0140 0.8237 0.6434
0.000 -0.2679 0.04336 0.03685 0.0120 0.8208 0.6439
0.250 -0.2316 0.04393 0.03732 0.0094 0.8191 0.6444
0.500 -0.1927 0.04491 0.03823 0.0062 0.8181 0.6450
0.750 -0.1999 0.04366 0.03695 0.0108 0.8076 0.6457
1.000 -0.1635 0.04416 0.03737 0.0081 0.8055 0.6463
1.250 -0.1219 0.04509 0.03823 0.0047 0.8042 0.6470
1.500 -0.1245 0.04417 0.03728 0.0083 0.7933 0.6478
1.750 -0.0821 0.04476 0.03782 0.0049 0.7909 0.6487
2.000 -0.0734 0.04440 0.03742 0.0068 0.7802 0.6497
2.250 -0.0104 0.04350 0.03644 0.0017 0.7640 0.6509
2.500 0.0144 0.04317 0.03606 0.0014 0.7529 0.6521
2.750 0.0577 0.04310 0.03595 -0.0017 0.7496 0.6534
3.000 0.1063 0.04314 0.03594 -0.0057 0.7479 0.6548
3.250 0.1088 0.04309 0.03587 -0.0031 0.7368 0.6562
3.500 0.1493 0.04311 0.03593 -0.0055 0.7348 0.6573
3.750 0.1569 0.04332 0.03618 -0.0033 0.7247 0.6584
4.000 0.1928 0.04335 0.03625 -0.0051 0.7220 0.6597
4.250 0.2110 0.04358 0.03652 -0.0045 0.7145 0.6610
4.500 0.2392 0.04364 0.03663 -0.0053 0.7098 0.6623
4.750 0.2773 0.04352 0.03656 -0.0074 0.7075 0.6639
5.000 0.3181 0.04338 0.03647 -0.0099 0.7061 0.6656
5.250 0.3244 0.04373 0.03685 -0.0078 0.6950 0.6672
5.500 0.3646 0.04342 0.03659 -0.0102 0.6931 0.6691
5.750 0.4070 0.04305 0.03628 -0.0127 0.6918 0.6709
6.000 0.4134 0.04337 0.03669 -0.0105 0.6803 0.6721
6.250 0.4544 0.04281 0.03626 -0.0125 0.6786 0.6738
6.500 0.4663 0.04305 0.03659 -0.0110 0.6681 0.6754
6.750 0.5087 0.04218 0.03586 -0.0129 0.6657 0.6777
7.000 0.5559 0.04097 0.03478 -0.0154 0.6642 0.6804
9.000 0.7977 0.03190 0.02686 -0.0155 0.5822 0.7002
9.250 0.8960 0.02517 0.01974 -0.0206 0.4737 0.7036
9.500 0.8868 0.02660 0.02054 -0.0157 0.3803 0.7060
9.750 0.8707 0.02881 0.02232 -0.0109 0.3097 0.7088
10.000 0.8577 0.03112 0.02418 -0.0069 0.2418 0.7117
10.250 0.8486 0.03337 0.02602 -0.0037 0.1777 0.7145
10.500 0.8434 0.03546 0.02777 -0.0008 0.1241 0.7166
10.750 0.8434 0.03733 0.02943 0.0014 0.0900 0.7192
11.000 0.8449 0.03921 0.03116 0.0034 0.0706 0.7222
11.250 0.8498 0.04095 0.03284 0.0050 0.0580 0.7256
11.500 0.8604 0.04231 0.03424 0.0059 0.0490 0.7292
11.750 0.8677 0.04387 0.03590 0.0074 0.0425 0.7320
12.000 0.8756 0.04548 0.03750 0.0086 0.0363 0.7354
12.250 0.8886 0.04684 0.03899 0.0095 0.0313 0.7396
12.500 0.8999 0.04836 0.04049 0.0102 0.0271 0.7438
12.750 0.9170 0.04966 0.04198 0.0111 0.0237 0.7474
13.000 0.9335 0.05094 0.04339 0.0117 0.0215 0.7521
13.250 0.9530 0.05268 0.04514 0.0118 0.0183 0.7574
13.500 0.9656 0.05426 0.04701 0.0128 0.0165 0.7616
13.750 0.9845 0.05607 0.04906 0.0132 0.0158 0.7668
14.000 0.9985 0.05825 0.05145 0.0137 0.0150 0.7724
14.250 1.0070 0.06074 0.05421 0.0147 0.0144 0.7770
14.500 1.0126 0.06365 0.05739 0.0155 0.0142 0.7824
14.750 1.0129 0.06708 0.06113 0.0165 0.0142 0.7875
15.000 1.0072 0.07092 0.06531 0.0177 0.0141 0.7919
15.250 0.9961 0.07543 0.07017 0.0188 0.0143 0.7968
15.500 0.9724 0.08139 0.07657 0.0197 0.0148 0.8009
15.750 0.9484 0.08732 0.08288 0.0200 0.0150 0.8043
16.000 0.9343 0.09196 0.08773 0.0195 0.0147 0.8099
16.250 0.8990 0.10058 0.09673 0.0179 0.0156 0.8130
16.500 0.8751 0.10757 0.10397 0.0156 0.0157 0.8173
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